NPL 9510 AIRFOIL (npl9510-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL 9510 AIRFOIL (npl9510-il) Reynolds number: 100,000 Max Cl/Cd: 18.37 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9510-il-100000.txt Download as CSV file: xf-npl9510-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9510 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7340 0.10970 0.10381 -0.0279 1.0000 0.0865
-12.500 -0.7251 0.10755 0.10166 -0.0274 1.0000 0.0875
-12.250 -0.9433 0.06977 0.06327 -0.0562 1.0000 0.0749
-12.000 -0.9642 0.06544 0.05875 -0.0571 1.0000 0.0745
-11.750 -0.9805 0.06126 0.05440 -0.0575 1.0000 0.0743
-11.500 -0.9918 0.05718 0.05006 -0.0577 1.0000 0.0742
-11.250 -0.9985 0.05336 0.04592 -0.0574 1.0000 0.0742
-11.000 -1.0004 0.04980 0.04200 -0.0569 1.0000 0.0744
-10.750 -0.9964 0.04630 0.03815 -0.0564 1.0000 0.0750
-10.500 -0.9831 0.04341 0.03522 -0.0557 1.0000 0.0766
-10.250 -0.9680 0.04149 0.03323 -0.0550 1.0000 0.0788
-10.000 -0.9536 0.03937 0.03090 -0.0544 1.0000 0.0812
-9.750 -0.9387 0.03708 0.02828 -0.0537 1.0000 0.0835
-9.500 -0.9218 0.03501 0.02578 -0.0530 1.0000 0.0857
-9.250 -0.9025 0.03294 0.02387 -0.0520 1.0000 0.0891
-9.000 -0.8832 0.03155 0.02239 -0.0513 1.0000 0.0940
-8.750 -0.8636 0.02988 0.02056 -0.0504 1.0000 0.0993
-8.500 -0.8436 0.02855 0.01934 -0.0495 1.0000 0.1056
-8.250 -0.8235 0.02711 0.01786 -0.0486 1.0000 0.1140
-8.000 -0.8026 0.02589 0.01660 -0.0481 1.0000 0.1256
-7.750 -0.7821 0.02454 0.01539 -0.0476 1.0000 0.1410
-7.500 -0.7612 0.02313 0.01421 -0.0473 1.0000 0.1617
-7.250 -0.7389 0.02170 0.01297 -0.0475 1.0000 0.1901
-7.000 -0.7151 0.02035 0.01188 -0.0480 1.0000 0.2238
-6.750 -0.6894 0.01907 0.01092 -0.0490 1.0000 0.2679
-6.500 -0.6627 0.01802 0.01036 -0.0500 1.0000 0.3326
-6.250 -0.6374 0.01793 0.01063 -0.0496 1.0000 0.4004
-6.000 -0.6135 0.01849 0.01125 -0.0483 1.0000 0.4452
-5.750 -0.5905 0.01922 0.01193 -0.0465 1.0000 0.4750
-5.500 -0.5700 0.02008 0.01282 -0.0439 1.0000 0.4940
-5.250 -0.5490 0.02080 0.01353 -0.0415 1.0000 0.5103
-5.000 -0.5271 0.02135 0.01402 -0.0396 1.0000 0.5254
-4.750 -0.5040 0.02174 0.01432 -0.0382 1.0000 0.5401
-4.500 -0.4871 0.02248 0.01514 -0.0344 1.0000 0.5471
-4.250 -0.4639 0.02266 0.01524 -0.0333 1.0000 0.5597
-4.000 -0.4449 0.02313 0.01572 -0.0305 1.0000 0.5684
-3.750 -0.4231 0.02330 0.01586 -0.0289 1.0000 0.5789
-3.500 -0.3973 0.02327 0.01574 -0.0288 1.0000 0.5922
-3.250 -0.3819 0.02373 0.01628 -0.0250 1.0000 0.5980
-3.000 -0.3553 0.02358 0.01604 -0.0252 1.0000 0.6106
-2.750 -0.3401 0.02399 0.01652 -0.0215 1.0000 0.6176
-2.500 -0.3173 0.02402 0.01654 -0.0204 1.0000 0.6298
-2.250 -0.2976 0.02418 0.01672 -0.0183 1.0000 0.6398
-2.000 -0.2740 0.02402 0.01656 -0.0176 1.0000 0.6481
-1.750 -0.2500 0.02385 0.01640 -0.0170 1.0000 0.6553
-1.500 -0.2199 0.02347 0.01597 -0.0185 1.0000 0.6633
-1.250 -0.1982 0.02335 0.01590 -0.0172 1.0000 0.6687
-1.000 -0.1676 0.02306 0.01559 -0.0188 1.0000 0.6765
-0.750 -0.1422 0.02284 0.01541 -0.0188 1.0000 0.6821
-0.500 -0.1179 0.02271 0.01533 -0.0184 1.0000 0.6877
-0.250 -0.0846 0.02248 0.01509 -0.0208 1.0000 0.6953
0.000 -0.0619 0.02235 0.01505 -0.0199 1.0000 0.6999
0.250 -0.0364 0.02226 0.01504 -0.0199 1.0000 0.7056
0.500 -0.0027 0.02214 0.01495 -0.0224 1.0000 0.7128
0.750 0.0189 0.02208 0.01503 -0.0213 1.0000 0.7172
1.000 0.0450 0.02206 0.01512 -0.0216 1.0000 0.7228
1.250 0.0770 0.02207 0.01522 -0.0235 1.0000 0.7296
1.500 0.0991 0.02208 0.01541 -0.0227 1.0000 0.7342
1.750 0.2989 0.02153 0.01205 -0.0461 0.1639 0.7415
2.000 0.3253 0.02225 0.01259 -0.0459 0.1367 0.7472
2.250 0.3480 0.02288 0.01314 -0.0446 0.1235 0.7520
2.500 0.3758 0.02361 0.01374 -0.0448 0.1144 0.7576
2.750 0.4064 0.02456 0.01463 -0.0453 0.1089 0.7633
3.000 0.4328 0.02522 0.01535 -0.0446 0.1031 0.7685
3.250 0.4638 0.02639 0.01642 -0.0453 0.0986 0.7747
3.500 0.4955 0.02790 0.01799 -0.0459 0.0965 0.7801
3.750 0.5230 0.02883 0.01921 -0.0452 0.0943 0.7855
4.000 0.5535 0.03013 0.02077 -0.0455 0.0917 0.7922
4.250 0.5812 0.03183 0.02278 -0.0449 0.0919 0.7978
4.500 0.6077 0.03384 0.02514 -0.0441 0.0928 0.8036
4.750 0.6364 0.03612 0.02779 -0.0442 0.0929 0.8102
5.000 0.6584 0.03868 0.03067 -0.0428 0.0948 0.8158
5.250 0.6994 0.05153 0.04651 -0.0421 0.2551 0.8193
5.500 0.7173 0.05416 0.04913 -0.0414 0.2342 0.8263
5.750 0.7301 0.05665 0.05165 -0.0397 0.2157 0.8324
6.000 0.7443 0.05939 0.05445 -0.0390 0.1981 0.8395
6.250 0.7524 0.06204 0.05731 -0.0379 0.1825 0.8461
6.500 0.7592 0.06547 0.06090 -0.0373 0.1709 0.8536
6.750 0.7744 0.06828 0.06373 -0.0363 0.1637 0.8614
7.000 0.7716 0.07220 0.06791 -0.0364 0.1540 0.8690
7.250 0.7818 0.07510 0.07087 -0.0355 0.1479 0.8776
7.500 0.8095 0.08008 0.07558 -0.0346 0.1446 0.8883
7.750 0.7695 0.08340 0.07949 -0.0363 0.1371 0.8966
8.000 0.7696 0.08668 0.08285 -0.0360 0.1326 0.9094
8.250 0.7985 0.08956 0.08564 -0.0329 0.1290 0.9278
8.500 0.7906 0.09513 0.09130 -0.0335 0.1270 0.9653
8.750 0.7427 0.10100 0.09735 -0.0425 0.1248 1.0000
9.000 0.7295 0.10771 0.10403 -0.0514 0.1203 1.0000
9.250 0.7395 0.11184 0.10813 -0.0533 0.1159 1.0000
9.500 0.6019 0.10909 0.10557 -0.0309 0.1269 0.9512
9.750 0.5633 0.11429 0.11074 -0.0377 0.1236 0.9766
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Polar data table (+)
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