NACA 63(2)A-015 (naca632a015-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63(2)A-015 (naca632a015-il) Reynolds number: 1,000,000 Max Cl/Cd: 84.88 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca632a015-il-1000000-n5.txt Download as CSV file: xf-naca632a015-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)A-015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.9410 0.08902 0.08654 -0.0380 1.0000 0.0058
-17.250 -0.9750 0.07862 0.07594 -0.0441 1.0000 0.0060
-17.000 -1.0117 0.06902 0.06612 -0.0494 1.0000 0.0058
-16.750 -1.0320 0.06270 0.05964 -0.0524 1.0000 0.0059
-16.500 -1.0437 0.05796 0.05474 -0.0542 1.0000 0.0060
-16.250 -1.0587 0.05313 0.04975 -0.0558 1.0000 0.0060
-16.000 -1.0644 0.04967 0.04616 -0.0566 1.0000 0.0060
-15.750 -1.0732 0.04606 0.04241 -0.0571 1.0000 0.0060
-15.500 -1.0780 0.04301 0.03922 -0.0571 1.0000 0.0060
-15.250 -1.0798 0.04040 0.03649 -0.0570 1.0000 0.0060
-15.000 -1.0796 0.03808 0.03405 -0.0565 1.0000 0.0061
-14.750 -1.0786 0.03591 0.03177 -0.0559 1.0000 0.0060
-14.500 -1.0705 0.03444 0.03021 -0.0552 1.0000 0.0062
-14.250 -1.0680 0.03251 0.02816 -0.0542 1.0000 0.0062
-14.000 -1.0620 0.03096 0.02650 -0.0532 1.0000 0.0062
-13.750 -1.0574 0.02936 0.02481 -0.0519 1.0000 0.0062
-13.500 -1.0481 0.02816 0.02351 -0.0507 1.0000 0.0063
-13.250 -1.0375 0.02711 0.02238 -0.0494 1.0000 0.0063
-13.000 -1.0288 0.02597 0.02116 -0.0478 1.0000 0.0063
-12.750 -1.0225 0.02468 0.01978 -0.0459 1.0000 0.0064
-12.500 -1.0145 0.02358 0.01860 -0.0439 1.0000 0.0065
-12.250 -1.0055 0.02262 0.01756 -0.0419 1.0000 0.0066
-12.000 -0.9951 0.02182 0.01671 -0.0398 1.0000 0.0067
-11.750 -0.9834 0.02118 0.01604 -0.0378 1.0000 0.0069
-11.500 -0.9731 0.02051 0.01532 -0.0353 1.0000 0.0070
-11.250 -0.9651 0.01980 0.01455 -0.0324 1.0000 0.0069
-11.000 -0.9559 0.01931 0.01403 -0.0295 1.0000 0.0070
-10.750 -0.9322 0.01861 0.01328 -0.0295 0.9934 0.0072
-10.250 -0.8743 0.01725 0.01182 -0.0315 0.9711 0.0074
-10.000 -0.8282 0.01650 0.01102 -0.0361 0.9586 0.0077
-9.750 -0.7750 0.01564 0.01008 -0.0423 0.9425 0.0079
-9.500 -0.7285 0.01500 0.00933 -0.0469 0.9175 0.0081
-9.250 -0.7042 0.01463 0.00882 -0.0466 0.8831 0.0083
-9.000 -0.6901 0.01434 0.00837 -0.0441 0.8533 0.0084
-8.750 -0.6770 0.01406 0.00797 -0.0413 0.8288 0.0086
-8.500 -0.6640 0.01368 0.00750 -0.0386 0.8112 0.0089
-8.250 -0.6465 0.01337 0.00712 -0.0367 0.7980 0.0091
-8.000 -0.6278 0.01310 0.00679 -0.0351 0.7864 0.0093
-7.750 -0.6086 0.01281 0.00644 -0.0335 0.7758 0.0097
-7.500 -0.5886 0.01253 0.00610 -0.0321 0.7667 0.0100
-7.250 -0.5676 0.01230 0.00581 -0.0309 0.7582 0.0104
-7.000 -0.5461 0.01206 0.00552 -0.0297 0.7504 0.0106
-6.750 -0.5253 0.01178 0.00519 -0.0284 0.7417 0.0112
-6.500 -0.5037 0.01151 0.00489 -0.0272 0.7346 0.0117
-6.250 -0.4814 0.01127 0.00462 -0.0262 0.7268 0.0123
-6.000 -0.4587 0.01106 0.00436 -0.0252 0.7195 0.0131
-5.750 -0.4354 0.01085 0.00413 -0.0244 0.7115 0.0138
-5.500 -0.4124 0.01065 0.00390 -0.0234 0.7038 0.0150
-5.250 -0.3885 0.01045 0.00370 -0.0227 0.6962 0.0170
-4.750 -0.3395 0.01016 0.00338 -0.0214 0.6814 0.0236
-4.500 -0.3148 0.01003 0.00324 -0.0208 0.6738 0.0262
-4.250 -0.2894 0.00992 0.00310 -0.0203 0.6669 0.0280
-4.000 -0.2644 0.00978 0.00295 -0.0197 0.6593 0.0299
-3.750 -0.2391 0.00968 0.00282 -0.0192 0.6530 0.0316
-3.500 -0.2133 0.00956 0.00269 -0.0188 0.6465 0.0332
-3.250 -0.1881 0.00945 0.00256 -0.0183 0.6397 0.0358
-3.000 -0.1622 0.00935 0.00245 -0.0179 0.6331 0.0379
-2.750 -0.1364 0.00925 0.00233 -0.0175 0.6263 0.0399
-2.500 -0.1108 0.00915 0.00223 -0.0170 0.6202 0.0439
-2.250 -0.0849 0.00903 0.00213 -0.0166 0.6138 0.0501
-2.000 -0.0594 0.00893 0.00204 -0.0162 0.6063 0.0604
-1.750 -0.0344 0.00878 0.00195 -0.0156 0.5969 0.0828
-1.500 -0.0173 0.00814 0.00169 -0.0137 0.5834 0.2272
-1.250 -0.0063 0.00714 0.00139 -0.0108 0.5679 0.4346
-1.000 0.0167 0.00698 0.00132 -0.0099 0.5523 0.4830
-0.750 0.0414 0.00688 0.00129 -0.0093 0.5404 0.5171
-0.500 0.0668 0.00680 0.00127 -0.0088 0.5315 0.5425
-0.250 0.0918 0.00675 0.00126 -0.0082 0.5223 0.5695
0.000 0.1175 0.00669 0.00126 -0.0077 0.5144 0.5924
0.250 0.1430 0.00668 0.00127 -0.0072 0.5061 0.6141
0.500 0.1694 0.00667 0.00128 -0.0069 0.4975 0.6304
0.750 0.1955 0.00670 0.00131 -0.0065 0.4875 0.6427
1.000 0.2223 0.00673 0.00133 -0.0063 0.4775 0.6517
1.250 0.2490 0.00677 0.00135 -0.0061 0.4683 0.6589
1.750 0.3020 0.00690 0.00142 -0.0056 0.4440 0.6725
2.000 0.3281 0.00699 0.00147 -0.0052 0.4288 0.6795
2.250 0.3538 0.00710 0.00153 -0.0049 0.4115 0.6856
2.500 0.3793 0.00721 0.00160 -0.0044 0.3944 0.6920
2.750 0.4046 0.00736 0.00168 -0.0040 0.3745 0.6988
3.000 0.4291 0.00752 0.00177 -0.0034 0.3510 0.7053
3.250 0.4530 0.00773 0.00189 -0.0027 0.3266 0.7124
3.500 0.4772 0.00794 0.00202 -0.0021 0.3040 0.7186
3.750 0.5012 0.00811 0.00214 -0.0014 0.2857 0.7254
4.000 0.5257 0.00829 0.00227 -0.0009 0.2703 0.7325
4.250 0.5493 0.00848 0.00241 -0.0002 0.2528 0.7398
4.500 0.5730 0.00867 0.00255 0.0005 0.2371 0.7476
4.750 0.5971 0.00883 0.00269 0.0011 0.2252 0.7551
5.000 0.6210 0.00899 0.00284 0.0018 0.2154 0.7635
5.250 0.6448 0.00914 0.00298 0.0025 0.2064 0.7721
5.500 0.6688 0.00927 0.00313 0.0031 0.1994 0.7820
5.750 0.6924 0.00940 0.00328 0.0038 0.1933 0.7923
6.250 0.7393 0.00963 0.00358 0.0054 0.1839 0.8170
6.500 0.7615 0.00977 0.00376 0.0063 0.1768 0.8314
6.750 0.7836 0.00990 0.00394 0.0074 0.1706 0.8479
7.000 0.8057 0.01002 0.00412 0.0084 0.1653 0.8676
7.250 0.8274 0.01018 0.00433 0.0094 0.1585 0.8916
7.500 0.8534 0.01034 0.00456 0.0095 0.1512 0.9164
7.750 0.8867 0.01061 0.00485 0.0079 0.1431 0.9377
8.000 0.9267 0.01097 0.00518 0.0048 0.1326 0.9520
8.250 0.9668 0.01139 0.00555 0.0015 0.1201 0.9618
8.500 1.0023 0.01187 0.00596 -0.0008 0.1050 0.9704
8.750 1.0350 0.01235 0.00638 -0.0026 0.0932 0.9771
9.000 1.0627 0.01278 0.00677 -0.0032 0.0854 0.9845
9.250 1.0908 0.01320 0.00717 -0.0039 0.0779 0.9913
9.500 1.1175 0.01373 0.00765 -0.0044 0.0690 0.9986
9.750 1.1384 0.01421 0.00810 -0.0037 0.0616 1.0000
10.000 1.1431 0.01458 0.00845 0.0004 0.0559 1.0000
10.250 1.1514 0.01494 0.00880 0.0038 0.0527 1.0000
10.500 1.1616 0.01534 0.00920 0.0066 0.0498 1.0000
10.750 1.1724 0.01580 0.00967 0.0092 0.0470 1.0000
11.000 1.1856 0.01622 0.01012 0.0113 0.0455 1.0000
11.250 1.1988 0.01669 0.01061 0.0132 0.0440 1.0000
11.500 1.2112 0.01725 0.01119 0.0152 0.0423 1.0000
11.750 1.2232 0.01787 0.01183 0.0170 0.0404 1.0000
12.000 1.2369 0.01846 0.01246 0.0185 0.0393 1.0000
12.250 1.2507 0.01908 0.01312 0.0199 0.0380 1.0000
12.500 1.2634 0.01979 0.01387 0.0212 0.0365 1.0000
12.750 1.2747 0.02065 0.01474 0.0226 0.0348 1.0000
13.000 1.2869 0.02149 0.01562 0.0238 0.0331 1.0000
13.250 1.2992 0.02237 0.01654 0.0248 0.0315 1.0000
13.500 1.3099 0.02340 0.01759 0.0259 0.0295 1.0000
13.750 1.3203 0.02450 0.01872 0.0268 0.0281 1.0000
14.000 1.3308 0.02563 0.01990 0.0276 0.0270 1.0000
14.250 1.3401 0.02689 0.02119 0.0284 0.0258 1.0000
14.500 1.3481 0.02829 0.02263 0.0291 0.0246 1.0000
14.750 1.3563 0.02972 0.02411 0.0298 0.0239 1.0000
15.000 1.3639 0.03124 0.02569 0.0303 0.0233 1.0000
15.250 1.3707 0.03285 0.02736 0.0308 0.0228 1.0000
15.500 1.3764 0.03461 0.02918 0.0311 0.0223 1.0000
15.750 1.3807 0.03655 0.03117 0.0314 0.0216 1.0000
16.000 1.3843 0.03859 0.03329 0.0316 0.0213 1.0000
16.250 1.3856 0.04094 0.03569 0.0317 0.0208 1.0000
16.500 1.3867 0.04339 0.03822 0.0317 0.0205 1.0000
16.750 1.3880 0.04587 0.04078 0.0315 0.0203 1.0000
17.000 1.3896 0.04840 0.04339 0.0312 0.0200 1.0000
17.250 1.3900 0.05113 0.04621 0.0308 0.0197 1.0000
17.500 1.3895 0.05402 0.04918 0.0303 0.0193 1.0000
17.750 1.3871 0.05721 0.05246 0.0296 0.0192 1.0000
18.000 1.3830 0.06068 0.05601 0.0287 0.0188 1.0000
18.250 1.3781 0.06434 0.05976 0.0276 0.0185 1.0000
18.500 1.3711 0.06834 0.06386 0.0264 0.0183 1.0000
18.750 1.3623 0.07267 0.06828 0.0250 0.0182 1.0000
19.000 1.3523 0.07726 0.07297 0.0234 0.0179 1.0000
19.250 1.3386 0.08248 0.07829 0.0215 0.0176 1.0000
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