NACA 63(2)-215 MOD B (n63215b-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63(2)-215 MOD B (n63215b-il) Reynolds number: 200,000 Max Cl/Cd: 47.85 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63215b-il-200000-n5.txt Download as CSV file: xf-n63215b-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)-215 MOD B
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7921 0.10984 0.10523 -0.0204 1.0000 0.0207
-16.250 -0.8386 0.09558 0.09065 -0.0298 1.0000 0.0205
-16.000 -0.8681 0.08597 0.08080 -0.0360 1.0000 0.0205
-15.750 -0.8901 0.07844 0.07303 -0.0405 1.0000 0.0206
-15.500 -0.9066 0.07231 0.06668 -0.0439 1.0000 0.0207
-15.250 -0.9209 0.06688 0.06101 -0.0467 1.0000 0.0209
-15.000 -0.9327 0.06212 0.05601 -0.0488 1.0000 0.0211
-14.750 -0.9392 0.05828 0.05199 -0.0502 1.0000 0.0213
-14.500 -0.9382 0.05554 0.04921 -0.0509 1.0000 0.0216
-14.250 -0.9371 0.05287 0.04646 -0.0516 1.0000 0.0218
-14.000 -0.9354 0.05032 0.04382 -0.0520 1.0000 0.0220
-13.750 -0.9325 0.04800 0.04142 -0.0523 1.0000 0.0223
-13.500 -0.9288 0.04581 0.03914 -0.0525 1.0000 0.0227
-13.250 -0.9244 0.04369 0.03693 -0.0524 1.0000 0.0231
-13.000 -0.9193 0.04170 0.03482 -0.0522 1.0000 0.0236
-12.750 -0.9131 0.03984 0.03283 -0.0519 1.0000 0.0242
-12.500 -0.9064 0.03803 0.03085 -0.0514 1.0000 0.0250
-12.250 -0.8980 0.03642 0.02912 -0.0509 1.0000 0.0257
-12.000 -0.8881 0.03501 0.02772 -0.0502 1.0000 0.0262
-11.750 -0.8779 0.03372 0.02641 -0.0496 1.0000 0.0268
-11.500 -0.8671 0.03247 0.02512 -0.0488 1.0000 0.0275
-11.250 -0.8557 0.03127 0.02387 -0.0479 1.0000 0.0283
-11.000 -0.8437 0.03013 0.02264 -0.0470 1.0000 0.0292
-10.750 -0.8311 0.02905 0.02146 -0.0459 1.0000 0.0300
-10.500 -0.8191 0.02796 0.02032 -0.0447 1.0000 0.0307
-10.250 -0.8085 0.02691 0.01931 -0.0434 1.0000 0.0315
-10.000 -0.7980 0.02601 0.01840 -0.0419 1.0000 0.0322
-9.750 -0.7885 0.02521 0.01759 -0.0400 1.0000 0.0332
-9.500 -0.7814 0.02449 0.01686 -0.0376 1.0000 0.0341
-9.250 -0.7585 0.02373 0.01602 -0.0379 0.9842 0.0357
-9.000 -0.7287 0.02269 0.01498 -0.0397 0.9648 0.0375
-8.750 -0.6983 0.02188 0.01415 -0.0413 0.9499 0.0396
-8.500 -0.6705 0.02115 0.01335 -0.0422 0.9351 0.0416
-8.000 -0.6264 0.01970 0.01181 -0.0416 0.9082 0.0452
-7.750 -0.6059 0.01912 0.01119 -0.0407 0.8960 0.0470
-7.500 -0.5852 0.01860 0.01059 -0.0398 0.8851 0.0490
-7.250 -0.5652 0.01806 0.01001 -0.0387 0.8750 0.0518
-7.000 -0.5445 0.01755 0.00947 -0.0377 0.8655 0.0553
-6.750 -0.5226 0.01712 0.00897 -0.0368 0.8577 0.0597
-6.500 -0.5014 0.01658 0.00845 -0.0359 0.8490 0.0657
-6.250 -0.4793 0.01610 0.00797 -0.0351 0.8417 0.0749
-6.000 -0.4567 0.01560 0.00753 -0.0344 0.8337 0.0910
-5.750 -0.4343 0.01507 0.00709 -0.0337 0.8267 0.1157
-5.500 -0.4117 0.01450 0.00667 -0.0331 0.8200 0.1494
-5.250 -0.3892 0.01386 0.00624 -0.0326 0.8133 0.1952
-5.000 -0.3671 0.01316 0.00580 -0.0320 0.8078 0.2604
-4.750 -0.3443 0.01249 0.00550 -0.0316 0.8007 0.3367
-4.500 -0.3196 0.01211 0.00534 -0.0311 0.7947 0.3981
-4.000 -0.2661 0.01180 0.00522 -0.0305 0.7827 0.4760
-3.750 -0.2390 0.01173 0.00517 -0.0301 0.7767 0.5016
-3.500 -0.2116 0.01168 0.00512 -0.0297 0.7679 0.5225
-3.250 -0.1842 0.01164 0.00503 -0.0292 0.7589 0.5387
-3.000 -0.1567 0.01161 0.00499 -0.0288 0.7478 0.5558
-2.750 -0.1293 0.01160 0.00495 -0.0284 0.7383 0.5715
-2.500 -0.1014 0.01156 0.00488 -0.0280 0.7285 0.5809
-2.250 -0.0729 0.01154 0.00480 -0.0279 0.7204 0.5898
-2.000 -0.0448 0.01150 0.00476 -0.0276 0.7125 0.5972
-1.750 -0.0163 0.01148 0.00468 -0.0275 0.7044 0.6043
-1.500 0.0121 0.01144 0.00460 -0.0274 0.6955 0.6105
-1.250 0.0404 0.01141 0.00457 -0.0272 0.6858 0.6165
-1.000 0.0689 0.01140 0.00446 -0.0270 0.6752 0.6237
-0.750 0.0968 0.01137 0.00444 -0.0267 0.6625 0.6297
-0.500 0.1251 0.01135 0.00439 -0.0266 0.6492 0.6364
-0.250 0.1533 0.01134 0.00432 -0.0264 0.6348 0.6426
0.000 0.1810 0.01134 0.00429 -0.0261 0.6184 0.6479
0.250 0.2090 0.01136 0.00425 -0.0259 0.5996 0.6546
0.500 0.2363 0.01140 0.00421 -0.0255 0.5735 0.6606
0.750 0.2628 0.01149 0.00419 -0.0250 0.5367 0.6667
1.000 0.2878 0.01174 0.00413 -0.0243 0.4675 0.6735
1.250 0.3081 0.01239 0.00427 -0.0231 0.3651 0.6791
1.500 0.3327 0.01279 0.00448 -0.0226 0.3370 0.6864
1.750 0.3585 0.01306 0.00468 -0.0222 0.3161 0.6932
2.000 0.3843 0.01332 0.00487 -0.0219 0.2976 0.6996
2.500 0.4361 0.01381 0.00523 -0.0212 0.2677 0.7128
2.750 0.4622 0.01405 0.00542 -0.0209 0.2549 0.7200
3.000 0.4883 0.01427 0.00560 -0.0206 0.2433 0.7265
3.250 0.5138 0.01451 0.00581 -0.0201 0.2330 0.7329
3.500 0.5399 0.01477 0.00601 -0.0199 0.2229 0.7404
3.750 0.5651 0.01499 0.00624 -0.0194 0.2146 0.7467
4.000 0.5905 0.01526 0.00648 -0.0190 0.2072 0.7547
4.250 0.6155 0.01550 0.00674 -0.0185 0.2009 0.7618
4.500 0.6408 0.01575 0.00699 -0.0181 0.1945 0.7699
4.750 0.6649 0.01606 0.00728 -0.0175 0.1889 0.7771
5.000 0.6900 0.01629 0.00756 -0.0170 0.1836 0.7849
5.250 0.7145 0.01655 0.00784 -0.0164 0.1781 0.7928
5.750 0.7621 0.01713 0.00845 -0.0152 0.1680 0.8089
6.000 0.7852 0.01741 0.00876 -0.0144 0.1631 0.8171
6.250 0.8075 0.01775 0.00910 -0.0135 0.1589 0.8258
6.500 0.8299 0.01807 0.00946 -0.0126 0.1553 0.8354
6.750 0.8521 0.01836 0.00982 -0.0117 0.1514 0.8450
7.250 0.8932 0.01906 0.01056 -0.0094 0.1440 0.8668
7.500 0.9129 0.01941 0.01095 -0.0081 0.1404 0.8795
7.750 0.9326 0.01969 0.01132 -0.0067 0.1366 0.8945
8.000 0.9504 0.01998 0.01168 -0.0051 0.1329 0.9137
8.250 0.9688 0.02034 0.01206 -0.0037 0.1296 0.9414
8.500 0.9950 0.02081 0.01254 -0.0041 0.1264 1.0000
8.750 1.0183 0.02128 0.01308 -0.0039 0.1234 1.0000
9.000 1.0397 0.02177 0.01360 -0.0034 0.1205 1.0000
9.250 1.0593 0.02230 0.01414 -0.0026 0.1179 1.0000
9.500 1.0773 0.02291 0.01473 -0.0017 0.1155 1.0000
9.750 1.0941 0.02364 0.01542 -0.0007 0.1132 1.0000
10.000 1.1135 0.02422 0.01609 0.0000 0.1113 1.0000
10.250 1.1319 0.02485 0.01679 0.0008 0.1089 1.0000
10.500 1.1492 0.02551 0.01751 0.0017 0.1066 1.0000
10.750 1.1654 0.02622 0.01826 0.0026 0.1044 1.0000
11.000 1.1802 0.02701 0.01907 0.0035 0.1024 1.0000
11.250 1.1938 0.02793 0.01997 0.0045 0.1005 1.0000
11.500 1.2086 0.02886 0.02095 0.0053 0.0989 1.0000
11.750 1.2239 0.02975 0.02195 0.0061 0.0974 1.0000
12.000 1.2381 0.03071 0.02301 0.0068 0.0957 1.0000
12.250 1.2514 0.03174 0.02413 0.0076 0.0941 1.0000
12.500 1.2638 0.03284 0.02529 0.0083 0.0926 1.0000
12.750 1.2752 0.03400 0.02653 0.0090 0.0912 1.0000
13.000 1.2855 0.03527 0.02785 0.0097 0.0898 1.0000
13.250 1.2949 0.03666 0.02927 0.0103 0.0886 1.0000
13.500 1.3037 0.03819 0.03081 0.0108 0.0873 1.0000
13.750 1.3125 0.03975 0.03247 0.0113 0.0862 1.0000
14.000 1.3203 0.04141 0.03428 0.0117 0.0851 1.0000
14.250 1.3267 0.04321 0.03622 0.0119 0.0839 1.0000
14.500 1.3321 0.04515 0.03829 0.0121 0.0826 1.0000
14.750 1.3365 0.04724 0.04049 0.0121 0.0815 1.0000
15.000 1.3400 0.04946 0.04282 0.0120 0.0804 1.0000
15.250 1.3424 0.05186 0.04533 0.0117 0.0795 1.0000
15.500 1.3438 0.05443 0.04800 0.0113 0.0787 1.0000
15.750 1.3443 0.05719 0.05085 0.0107 0.0778 1.0000
16.000 1.3441 0.06013 0.05386 0.0099 0.0770 1.0000
16.250 1.3436 0.06322 0.05703 0.0090 0.0762 1.0000
16.500 1.3438 0.06634 0.06021 0.0082 0.0753 1.0000
16.750 1.3365 0.07059 0.06463 0.0064 0.0746 1.0000
17.000 1.3240 0.07585 0.07010 0.0039 0.0741 1.0000
17.250 1.3063 0.08222 0.07671 0.0004 0.0734 1.0000
17.500 1.2815 0.09020 0.08493 -0.0042 0.0727 1.0000
17.750 1.2368 0.10251 0.09756 -0.0120 0.0720 1.0000
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Polar data table (+)
Polar graphs
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