NACA 63(3)-218 (naca633218-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 63(3)-218 (naca633218-il) Reynolds number: 500,000 Max Cl/Cd: 63.9 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca633218-il-500000-n5.txt Download as CSV file: xf-naca633218-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(3)-218
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.500 -1.0606 0.10064 0.09632 -0.0296 1.0000 0.0185
-19.250 -1.0662 0.09601 0.09161 -0.0320 1.0000 0.0186
-19.000 -1.0712 0.09155 0.08708 -0.0342 1.0000 0.0189
-18.750 -1.0743 0.08745 0.08291 -0.0362 1.0000 0.0192
-18.500 -1.0770 0.08349 0.07888 -0.0381 1.0000 0.0194
-18.250 -1.0779 0.07986 0.07518 -0.0397 1.0000 0.0197
-18.000 -1.0781 0.07641 0.07165 -0.0412 1.0000 0.0201
-17.750 -1.0779 0.07308 0.06825 -0.0426 1.0000 0.0204
-17.500 -1.0759 0.07003 0.06512 -0.0438 1.0000 0.0210
-17.250 -1.0753 0.06689 0.06190 -0.0449 1.0000 0.0212
-17.000 -1.0712 0.06422 0.05913 -0.0459 1.0000 0.0217
-16.750 -1.0429 0.06024 0.05480 -0.0538 0.8555 0.0223
-16.500 -1.0428 0.05774 0.05207 -0.0540 0.8093 0.0226
-16.250 -1.0397 0.05535 0.04954 -0.0544 0.7855 0.0231
-16.000 -1.0357 0.05319 0.04721 -0.0547 0.7564 0.0235
-15.750 -1.0313 0.05103 0.04490 -0.0550 0.7321 0.0239
-15.500 -1.0263 0.04900 0.04270 -0.0552 0.7033 0.0244
-15.250 -1.0202 0.04712 0.04063 -0.0553 0.6742 0.0249
-15.000 -1.0136 0.04531 0.03865 -0.0554 0.6453 0.0254
-14.750 -1.0079 0.04437 0.03686 -0.0550 0.3773 0.0259
-14.500 -1.0043 0.04236 0.03472 -0.0550 0.3302 0.0265
-14.250 -0.9988 0.04052 0.03282 -0.0550 0.3263 0.0269
-14.000 -0.9913 0.03892 0.03116 -0.0549 0.3222 0.0276
-13.500 -0.9750 0.03591 0.02802 -0.0544 0.3180 0.0288
-13.250 -0.9659 0.03452 0.02656 -0.0541 0.3171 0.0294
-13.000 -0.9563 0.03321 0.02518 -0.0537 0.3161 0.0300
-12.750 -0.9467 0.03193 0.02383 -0.0532 0.3151 0.0305
-12.500 -0.9403 0.03043 0.02229 -0.0525 0.3145 0.0311
-12.250 -0.9316 0.02914 0.02096 -0.0519 0.3140 0.0318
-12.000 -0.9219 0.02796 0.01974 -0.0512 0.3131 0.0324
-11.750 -0.9113 0.02687 0.01860 -0.0505 0.3125 0.0332
-11.500 -0.8998 0.02587 0.01755 -0.0497 0.3120 0.0341
-11.250 -0.8878 0.02493 0.01655 -0.0489 0.3114 0.0349
-11.000 -0.8754 0.02405 0.01560 -0.0481 0.3108 0.0355
-10.750 -0.8657 0.02302 0.01455 -0.0470 0.3104 0.0365
-10.500 -0.8546 0.02213 0.01362 -0.0459 0.3099 0.0375
-10.250 -0.8425 0.02133 0.01279 -0.0448 0.3093 0.0387
-10.000 -0.8297 0.02061 0.01202 -0.0436 0.3089 0.0398
-9.750 -0.8164 0.01996 0.01132 -0.0423 0.3085 0.0411
-9.500 -0.8060 0.01927 0.01060 -0.0406 0.3081 0.0426
-9.250 -0.7977 0.01872 0.01003 -0.0383 0.3079 0.0441
-9.000 -0.7843 0.01828 0.00956 -0.0366 0.3075 0.0463
-8.750 -0.7669 0.01786 0.00910 -0.0355 0.3072 0.0488
-8.500 -0.7489 0.01743 0.00865 -0.0344 0.3068 0.0517
-7.750 -0.6875 0.01626 0.00747 -0.0322 0.3060 0.0674
-7.500 -0.6658 0.01587 0.00710 -0.0316 0.3059 0.0768
-7.250 -0.6438 0.01546 0.00673 -0.0311 0.3057 0.0893
-7.000 -0.6214 0.01505 0.00638 -0.0307 0.3056 0.1051
-6.750 -0.5981 0.01467 0.00605 -0.0303 0.3055 0.1223
-6.500 -0.5746 0.01428 0.00573 -0.0300 0.3053 0.1414
-6.250 -0.5507 0.01388 0.00541 -0.0298 0.3052 0.1641
-6.000 -0.5268 0.01346 0.00510 -0.0295 0.3051 0.1913
-5.750 -0.5029 0.01298 0.00477 -0.0294 0.3047 0.2282
-5.500 -0.4786 0.01250 0.00445 -0.0292 0.3041 0.2702
-5.250 -0.4536 0.01207 0.00418 -0.0292 0.3034 0.3096
-5.000 -0.4277 0.01174 0.00397 -0.0292 0.3028 0.3458
-4.750 -0.4010 0.01151 0.00383 -0.0293 0.3024 0.3786
-4.500 -0.3739 0.01132 0.00374 -0.0294 0.3022 0.4125
-4.250 -0.3463 0.01120 0.00368 -0.0296 0.3020 0.4367
-4.000 -0.3181 0.01115 0.00364 -0.0297 0.3018 0.4520
-3.750 -0.2896 0.01113 0.00360 -0.0299 0.3016 0.4630
-3.500 -0.2612 0.01110 0.00357 -0.0301 0.3014 0.4721
-3.250 -0.2326 0.01111 0.00354 -0.0303 0.3012 0.4813
-3.000 -0.2042 0.01109 0.00354 -0.0305 0.3010 0.4917
-2.750 -0.1754 0.01112 0.00353 -0.0307 0.3006 0.5009
-2.500 -0.1470 0.01112 0.00352 -0.0309 0.3001 0.5069
-2.250 -0.1183 0.01114 0.00352 -0.0311 0.2997 0.5125
-2.000 -0.0895 0.01117 0.00351 -0.0314 0.2993 0.5177
-1.750 -0.0609 0.01119 0.00352 -0.0316 0.2987 0.5226
-1.500 -0.0324 0.01122 0.00354 -0.0318 0.2983 0.5278
-1.250 -0.0037 0.01126 0.00356 -0.0320 0.2980 0.5332
-1.000 0.0250 0.01132 0.00358 -0.0322 0.2977 0.5383
-0.750 0.0534 0.01135 0.00363 -0.0324 0.2974 0.5433
-0.500 0.0819 0.01140 0.00367 -0.0326 0.2971 0.5482
-0.250 0.1105 0.01146 0.00371 -0.0328 0.2968 0.5531
0.000 0.1390 0.01153 0.00376 -0.0330 0.2965 0.5573
0.250 0.1673 0.01159 0.00383 -0.0331 0.2961 0.5615
0.500 0.1955 0.01166 0.00391 -0.0333 0.2958 0.5661
0.750 0.2238 0.01176 0.00399 -0.0335 0.2954 0.5711
1.000 0.2521 0.01186 0.00407 -0.0336 0.2950 0.5755
1.250 0.2800 0.01195 0.00418 -0.0338 0.2946 0.5800
1.500 0.3084 0.01202 0.00427 -0.0339 0.2943 0.5846
1.750 0.3370 0.01207 0.00433 -0.0341 0.2940 0.5893
2.250 0.3938 0.01217 0.00449 -0.0345 0.2933 0.5985
2.500 0.4221 0.01222 0.00458 -0.0346 0.2929 0.6039
2.750 0.4504 0.01229 0.00467 -0.0348 0.2924 0.6090
3.000 0.4787 0.01234 0.00476 -0.0350 0.2917 0.6136
3.250 0.5070 0.01237 0.00484 -0.0351 0.2903 0.6183
3.500 0.5351 0.01243 0.00495 -0.0353 0.2893 0.6234
3.750 0.5631 0.01251 0.00505 -0.0354 0.2884 0.6287
4.000 0.5910 0.01258 0.00516 -0.0355 0.2874 0.6338
4.250 0.6188 0.01263 0.00526 -0.0356 0.2858 0.6394
4.500 0.6463 0.01271 0.00537 -0.0356 0.2840 0.6451
5.000 0.7034 0.01268 0.00550 -0.0360 0.2777 0.6553
5.250 0.7319 0.01266 0.00555 -0.0362 0.2727 0.6613
5.500 0.7615 0.01255 0.00526 -0.0366 0.2130 0.6674
5.750 0.7831 0.01304 0.00569 -0.0359 0.1997 0.6728
6.000 0.8063 0.01338 0.00605 -0.0353 0.1918 0.6785
6.250 0.8296 0.01371 0.00641 -0.0348 0.1864 0.6846
6.500 0.8535 0.01398 0.00672 -0.0343 0.1831 0.6904
6.750 0.8782 0.01417 0.00698 -0.0340 0.1793 0.6967
7.000 0.9016 0.01444 0.00729 -0.0334 0.1744 0.7032
7.250 0.9250 0.01470 0.00758 -0.0329 0.1693 0.7090
7.500 0.9481 0.01493 0.00787 -0.0323 0.1615 0.7155
7.750 0.9706 0.01519 0.00816 -0.0317 0.1513 0.7225
8.000 0.9899 0.01561 0.00850 -0.0306 0.1312 0.7288
8.250 1.0043 0.01611 0.00894 -0.0288 0.1132 0.7354
8.500 1.0158 0.01665 0.00944 -0.0265 0.1011 0.7427
8.750 1.0268 0.01727 0.01005 -0.0243 0.0911 0.7498
9.000 1.0367 0.01796 0.01075 -0.0221 0.0812 0.7578
9.500 1.0567 0.01951 0.01231 -0.0183 0.0646 0.7735
9.750 1.0665 0.02037 0.01319 -0.0166 0.0586 0.7825
10.000 1.0751 0.02132 0.01417 -0.0149 0.0532 0.7915
10.250 1.0846 0.02230 0.01519 -0.0134 0.0492 0.8014
10.500 1.0931 0.02334 0.01629 -0.0119 0.0458 0.8112
10.750 1.1024 0.02440 0.01741 -0.0106 0.0433 0.8224
11.250 1.1177 0.02676 0.01992 -0.0079 0.0389 0.8490
11.500 1.1248 0.02800 0.02126 -0.0066 0.0372 0.8658
11.750 1.1299 0.02935 0.02271 -0.0051 0.0357 0.8899
12.000 1.1388 0.03076 0.02427 -0.0046 0.0347 0.9401
12.500 1.1588 0.03385 0.02747 -0.0044 0.0327 1.0000
12.750 1.1658 0.03559 0.02926 -0.0040 0.0319 1.0000
13.000 1.1718 0.03745 0.03116 -0.0037 0.0310 1.0000
13.250 1.1767 0.03946 0.03321 -0.0034 0.0303 1.0000
13.500 1.1806 0.04165 0.03544 -0.0032 0.0296 1.0000
13.750 1.1873 0.04363 0.03748 -0.0032 0.0290 1.0000
14.000 1.1932 0.04574 0.03966 -0.0032 0.0285 1.0000
14.250 1.1988 0.04794 0.04192 -0.0033 0.0278 1.0000
14.500 1.2036 0.05028 0.04431 -0.0035 0.0271 1.0000
14.750 1.2076 0.05275 0.04683 -0.0038 0.0265 1.0000
15.000 1.2110 0.05536 0.04949 -0.0041 0.0259 1.0000
15.250 1.2129 0.05819 0.05236 -0.0046 0.0254 1.0000
15.500 1.2158 0.06096 0.05520 -0.0052 0.0250 1.0000
15.750 1.2211 0.06349 0.05780 -0.0057 0.0244 1.0000
16.000 1.2256 0.06617 0.06056 -0.0064 0.0238 1.0000
16.250 1.2296 0.06896 0.06342 -0.0071 0.0233 1.0000
16.500 1.2330 0.07185 0.06636 -0.0080 0.0228 1.0000
16.750 1.2356 0.07490 0.06947 -0.0089 0.0222 1.0000
17.000 1.2379 0.07805 0.07267 -0.0099 0.0217 1.0000
17.250 1.2387 0.08145 0.07611 -0.0111 0.0212 1.0000
17.500 1.2430 0.08441 0.07915 -0.0121 0.0208 1.0000
17.750 1.2468 0.08744 0.08227 -0.0132 0.0203 1.0000
18.000 1.2499 0.09064 0.08554 -0.0144 0.0198 1.0000
18.250 1.2531 0.09384 0.08881 -0.0157 0.0193 1.0000
18.500 1.2553 0.09724 0.09227 -0.0172 0.0189 1.0000
18.750 1.2575 0.10066 0.09575 -0.0186 0.0185 1.0000
19.000 1.2581 0.10436 0.09951 -0.0203 0.0181 1.0000
19.250 1.2579 0.10823 0.10342 -0.0221 0.0177 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 63(3)-218 (naca633218-il)