NPL 9615 AIRFOIL (npl9615-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9615 AIRFOIL (npl9615-il) Reynolds number: 200,000 Max Cl/Cd: 52.36 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9615-il-200000-n5.txt Download as CSV file: xf-npl9615-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9615 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6299 0.08643 0.08247 -0.0229 1.0000 0.0201
-10.500 -0.6634 0.07270 0.06870 -0.0344 1.0000 0.0197
-10.250 -0.6998 0.06416 0.06000 -0.0394 1.0000 0.0194
-10.000 -0.7313 0.05856 0.05421 -0.0387 1.0000 0.0192
-9.750 -0.7592 0.05321 0.04862 -0.0358 1.0000 0.0190
-9.500 -0.7894 0.04595 0.04089 -0.0318 1.0000 0.0187
-9.250 -0.8189 0.03761 0.03181 -0.0263 1.0000 0.0184
-9.000 -0.8219 0.03335 0.02703 -0.0226 1.0000 0.0184
-8.750 -0.8149 0.03060 0.02392 -0.0198 1.0000 0.0185
-8.500 -0.8034 0.02851 0.02155 -0.0175 1.0000 0.0186
-8.250 -0.7893 0.02681 0.01960 -0.0154 1.0000 0.0188
-8.000 -0.7738 0.02533 0.01791 -0.0135 1.0000 0.0190
-7.750 -0.7573 0.02402 0.01642 -0.0116 1.0000 0.0193
-7.500 -0.7402 0.02284 0.01508 -0.0098 1.0000 0.0196
-7.250 -0.7228 0.02177 0.01386 -0.0080 1.0000 0.0201
-7.000 -0.7053 0.02078 0.01274 -0.0062 1.0000 0.0205
-6.750 -0.6877 0.01997 0.01184 -0.0044 1.0000 0.0211
-6.500 -0.6691 0.01947 0.01131 -0.0028 1.0000 0.0217
-6.250 -0.6505 0.01896 0.01078 -0.0012 1.0000 0.0225
-6.000 -0.6321 0.01840 0.01015 0.0005 1.0000 0.0236
-5.750 -0.6133 0.01790 0.00961 0.0021 1.0000 0.0249
-5.500 -0.5840 0.01743 0.00909 0.0016 0.9976 0.0271
-5.250 -0.5496 0.01697 0.00857 0.0000 0.9932 0.0297
-5.000 -0.5144 0.01653 0.00805 -0.0018 0.9889 0.0327
-4.750 -0.4824 0.01613 0.00762 -0.0029 0.9829 0.0350
-4.500 -0.4482 0.01573 0.00717 -0.0044 0.9772 0.0374
-4.250 -0.4125 0.01543 0.00684 -0.0062 0.9721 0.0407
-4.000 -0.3809 0.01507 0.00649 -0.0071 0.9648 0.0430
-3.750 -0.3451 0.01470 0.00609 -0.0089 0.9594 0.0454
-3.500 -0.3106 0.01434 0.00573 -0.0104 0.9533 0.0477
-3.250 -0.2781 0.01402 0.00539 -0.0114 0.9452 0.0504
-3.000 -0.2417 0.01369 0.00507 -0.0133 0.9396 0.0543
-2.750 -0.2128 0.01342 0.00480 -0.0135 0.9285 0.0587
-2.500 -0.1796 0.01312 0.00449 -0.0146 0.9198 0.0635
-2.250 -0.1486 0.01281 0.00420 -0.0152 0.9086 0.0683
-2.000 -0.1178 0.01252 0.00393 -0.0157 0.8964 0.0757
-1.750 -0.0869 0.01218 0.00365 -0.0163 0.8831 0.0945
-1.500 -0.0740 0.01037 0.00324 -0.0141 0.8668 0.4362
-1.250 -0.0566 0.00967 0.00317 -0.0117 0.8482 0.5904
-1.000 -0.0358 0.00929 0.00317 -0.0097 0.8263 0.6866
-0.750 -0.0093 0.00908 0.00313 -0.0088 0.8051 0.7541
-0.500 0.0230 0.00900 0.00315 -0.0089 0.7856 0.8001
-0.250 0.0532 0.00910 0.00323 -0.0085 0.7649 0.8522
0.000 0.0841 0.00925 0.00332 -0.0085 0.7430 0.8852
0.250 0.1186 0.00940 0.00339 -0.0094 0.7208 0.9014
0.500 0.1498 0.00951 0.00338 -0.0098 0.6995 0.9115
0.750 0.1823 0.00963 0.00340 -0.0105 0.6797 0.9204
1.000 0.2120 0.00975 0.00341 -0.0108 0.6592 0.9301
1.250 0.2464 0.00990 0.00344 -0.0119 0.6328 0.9368
1.500 0.2752 0.01006 0.00346 -0.0120 0.6061 0.9461
1.750 0.3096 0.01024 0.00349 -0.0133 0.5769 0.9516
2.000 0.3448 0.01043 0.00354 -0.0148 0.5494 0.9567
2.250 0.3771 0.01061 0.00362 -0.0157 0.5230 0.9633
2.500 0.4086 0.01080 0.00369 -0.0165 0.4986 0.9696
2.750 0.4443 0.01096 0.00377 -0.0183 0.4752 0.9745
3.000 0.4777 0.01114 0.00387 -0.0196 0.4519 0.9804
3.250 0.5089 0.01135 0.00400 -0.0204 0.4285 0.9864
3.500 0.5433 0.01154 0.00411 -0.0220 0.4024 0.9908
3.750 0.5774 0.01176 0.00423 -0.0236 0.3729 0.9954
4.000 0.6111 0.01203 0.00440 -0.0251 0.3414 0.9996
4.250 0.6336 0.01231 0.00457 -0.0243 0.3106 1.0000
4.500 0.6540 0.01264 0.00476 -0.0230 0.2803 1.0000
5.000 0.6940 0.01335 0.00527 -0.0204 0.2322 1.0000
5.250 0.7143 0.01368 0.00555 -0.0191 0.2129 1.0000
5.500 0.7342 0.01403 0.00585 -0.0177 0.1974 1.0000
5.750 0.7540 0.01440 0.00616 -0.0163 0.1828 1.0000
6.000 0.7733 0.01481 0.00650 -0.0149 0.1670 1.0000
6.250 0.7928 0.01520 0.00684 -0.0135 0.1506 1.0000
6.500 0.8122 0.01561 0.00719 -0.0121 0.1371 1.0000
6.750 0.8319 0.01600 0.00756 -0.0107 0.1271 1.0000
7.000 0.8519 0.01637 0.00795 -0.0093 0.1178 1.0000
7.250 0.8716 0.01677 0.00835 -0.0080 0.1081 1.0000
7.500 0.8909 0.01722 0.00878 -0.0065 0.0978 1.0000
7.750 0.9108 0.01762 0.00923 -0.0052 0.0854 1.0000
8.000 0.9291 0.01815 0.00970 -0.0037 0.0739 1.0000
8.250 0.9464 0.01878 0.01029 -0.0020 0.0628 1.0000
8.500 0.9630 0.01947 0.01096 -0.0003 0.0526 1.0000
8.750 0.9791 0.02021 0.01167 0.0015 0.0452 1.0000
9.000 0.9953 0.02093 0.01241 0.0033 0.0400 1.0000
9.250 1.0112 0.02168 0.01318 0.0050 0.0364 1.0000
9.500 1.0265 0.02246 0.01399 0.0068 0.0337 1.0000
9.750 1.0414 0.02325 0.01486 0.0086 0.0317 1.0000
10.000 1.0553 0.02410 0.01578 0.0105 0.0302 1.0000
10.250 1.0686 0.02498 0.01673 0.0124 0.0289 1.0000
10.500 1.0798 0.02595 0.01775 0.0145 0.0279 1.0000
10.750 1.0903 0.02689 0.01882 0.0167 0.0269 1.0000
11.000 1.0985 0.02791 0.01992 0.0192 0.0261 1.0000
11.250 1.1056 0.02902 0.02110 0.0216 0.0254 1.0000
11.500 1.1111 0.03030 0.02242 0.0238 0.0248 1.0000
11.750 1.1178 0.03163 0.02389 0.0257 0.0242 1.0000
12.000 1.1234 0.03310 0.02549 0.0275 0.0237 1.0000
12.250 1.1283 0.03471 0.02720 0.0289 0.0232 1.0000
12.500 1.1326 0.03646 0.02903 0.0301 0.0227 1.0000
12.750 1.1360 0.03837 0.03101 0.0311 0.0223 1.0000
13.000 1.1386 0.04048 0.03318 0.0318 0.0220 1.0000
13.250 1.1409 0.04277 0.03565 0.0322 0.0216 1.0000
13.500 1.1423 0.04527 0.03831 0.0324 0.0212 1.0000
13.750 1.1427 0.04797 0.04116 0.0323 0.0208 1.0000
14.000 1.1422 0.05087 0.04419 0.0319 0.0205 1.0000
14.250 1.1409 0.05398 0.04743 0.0313 0.0202 1.0000
14.500 1.1387 0.05730 0.05086 0.0304 0.0200 1.0000
14.750 1.1357 0.06079 0.05446 0.0293 0.0198 1.0000
15.000 1.1320 0.06448 0.05827 0.0281 0.0196 1.0000
15.250 1.1276 0.06831 0.06220 0.0268 0.0195 1.0000
15.500 1.1229 0.07227 0.06626 0.0253 0.0194 1.0000
15.750 1.1144 0.07702 0.07116 0.0232 0.0193 1.0000
16.000 1.1031 0.08243 0.07675 0.0206 0.0192 1.0000
16.250 1.0904 0.08832 0.08283 0.0176 0.0191 1.0000
16.500 1.0762 0.09470 0.08939 0.0141 0.0191 1.0000
16.750 1.0604 0.10166 0.09654 0.0102 0.0191 1.0000
17.000 1.0427 0.10926 0.10432 0.0059 0.0191 1.0000
17.250 1.0229 0.11772 0.11296 0.0008 0.0191 1.0000
17.500 1.0002 0.12719 0.12261 -0.0049 0.0191 1.0000
17.750 0.9716 0.13864 0.13424 -0.0119 0.0192 1.0000
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