NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Reynolds number: 500,000 Max Cl/Cd: 54.55 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nplx-il-500000-n5.txt Download as CSV file: xf-nplx-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NPL AIRFOIL FROM ARC CP 1372
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8934 0.07537 0.07216 -0.0398 1.0000 0.0081
-13.750 -0.9346 0.06383 0.06035 -0.0471 1.0000 0.0081
-13.500 -0.9546 0.05748 0.05379 -0.0504 1.0000 0.0080
-13.250 -0.9756 0.05161 0.04773 -0.0530 1.0000 0.0081
-13.000 -0.9863 0.04749 0.04342 -0.0544 1.0000 0.0080
-12.750 -0.9992 0.04338 0.03913 -0.0553 1.0000 0.0081
-12.500 -1.0043 0.04040 0.03599 -0.0555 1.0000 0.0080
-12.250 -1.0091 0.03764 0.03307 -0.0552 1.0000 0.0081
-12.000 -1.0118 0.03526 0.03054 -0.0545 1.0000 0.0081
-11.750 -1.0147 0.03309 0.02822 -0.0533 1.0000 0.0081
-11.500 -1.0150 0.03141 0.02640 -0.0516 1.0000 0.0081
-11.250 -1.0186 0.02990 0.02477 -0.0489 1.0000 0.0081
-11.000 -1.0191 0.02856 0.02331 -0.0459 1.0000 0.0082
-10.750 -1.0128 0.02724 0.02186 -0.0437 1.0000 0.0082
-10.500 -1.0039 0.02608 0.02060 -0.0417 1.0000 0.0083
-10.250 -0.9932 0.02499 0.01940 -0.0398 1.0000 0.0083
-10.000 -0.9809 0.02398 0.01828 -0.0381 1.0000 0.0084
-9.750 -0.9676 0.02301 0.01721 -0.0364 1.0000 0.0085
-9.500 -0.9531 0.02212 0.01624 -0.0348 1.0000 0.0086
-9.250 -0.9378 0.02127 0.01530 -0.0332 1.0000 0.0086
-9.000 -0.9217 0.02048 0.01443 -0.0317 1.0000 0.0088
-8.750 -0.9051 0.01972 0.01360 -0.0303 1.0000 0.0089
-8.500 -0.8878 0.01903 0.01282 -0.0288 1.0000 0.0091
-8.250 -0.8633 0.01828 0.01200 -0.0289 0.9992 0.0092
-8.000 -0.8338 0.01756 0.01121 -0.0300 0.9975 0.0094
-7.750 -0.8038 0.01688 0.01046 -0.0311 0.9956 0.0096
-7.500 -0.7732 0.01625 0.00975 -0.0323 0.9939 0.0099
-7.250 -0.7448 0.01567 0.00911 -0.0330 0.9916 0.0101
-7.000 -0.7157 0.01508 0.00848 -0.0337 0.9892 0.0104
-6.750 -0.6857 0.01454 0.00792 -0.0347 0.9870 0.0109
-6.500 -0.6544 0.01406 0.00740 -0.0359 0.9851 0.0115
-6.250 -0.6233 0.01361 0.00693 -0.0370 0.9831 0.0121
-6.000 -0.5956 0.01319 0.00648 -0.0373 0.9793 0.0129
-5.750 -0.5654 0.01275 0.00604 -0.0381 0.9764 0.0145
-5.500 -0.5338 0.01239 0.00566 -0.0392 0.9741 0.0165
-5.250 -0.5014 0.01202 0.00531 -0.0405 0.9724 0.0194
-5.000 -0.4748 0.01171 0.00501 -0.0404 0.9676 0.0225
-4.750 -0.4444 0.01141 0.00472 -0.0412 0.9641 0.0263
-4.500 -0.4123 0.01112 0.00444 -0.0423 0.9614 0.0296
-4.250 -0.3793 0.01082 0.00417 -0.0436 0.9595 0.0339
-4.000 -0.3517 0.01059 0.00392 -0.0436 0.9541 0.0371
-3.750 -0.3208 0.01030 0.00366 -0.0444 0.9503 0.0414
-3.500 -0.2875 0.01005 0.00343 -0.0457 0.9476 0.0468
-3.250 -0.2528 0.00979 0.00319 -0.0473 0.9453 0.0540
-2.750 -0.1912 0.00923 0.00280 -0.0489 0.9349 0.0877
-2.500 -0.1576 0.00891 0.00259 -0.0503 0.9314 0.1144
-2.250 -0.1274 0.00846 0.00237 -0.0511 0.9259 0.1755
-2.000 -0.1014 0.00698 0.00189 -0.0520 0.9191 0.4528
-1.750 -0.0686 0.00683 0.00183 -0.0530 0.9133 0.4946
-1.500 -0.0375 0.00675 0.00177 -0.0536 0.9034 0.5166
-1.250 -0.0068 0.00670 0.00172 -0.0540 0.8916 0.5347
-1.000 0.0232 0.00667 0.00170 -0.0543 0.8790 0.5520
-0.750 0.0525 0.00666 0.00167 -0.0544 0.8665 0.5626
-0.500 0.0811 0.00667 0.00163 -0.0544 0.8542 0.5682
-0.250 0.1094 0.00669 0.00159 -0.0542 0.8381 0.5739
0.000 0.1368 0.00672 0.00158 -0.0539 0.8189 0.5804
0.500 0.1905 0.00683 0.00158 -0.0530 0.7788 0.5933
0.750 0.2167 0.00690 0.00157 -0.0524 0.7534 0.5974
1.000 0.2411 0.00705 0.00155 -0.0514 0.7063 0.6011
1.250 0.2582 0.00759 0.00155 -0.0489 0.5742 0.6043
1.500 0.2755 0.00835 0.00173 -0.0469 0.4312 0.6075
1.750 0.2967 0.00894 0.00190 -0.0457 0.3268 0.6112
2.000 0.3202 0.00939 0.00205 -0.0450 0.2504 0.6152
2.250 0.3426 0.00998 0.00223 -0.0441 0.1516 0.6192
2.500 0.3668 0.01037 0.00243 -0.0434 0.0998 0.6230
2.750 0.3927 0.01060 0.00259 -0.0430 0.0822 0.6277
3.000 0.4190 0.01079 0.00274 -0.0426 0.0706 0.6327
3.250 0.4454 0.01098 0.00290 -0.0423 0.0614 0.6374
3.500 0.4716 0.01116 0.00308 -0.0419 0.0539 0.6422
3.750 0.4975 0.01139 0.00326 -0.0415 0.0477 0.6475
4.000 0.5239 0.01158 0.00346 -0.0411 0.0443 0.6525
4.250 0.5497 0.01180 0.00369 -0.0406 0.0412 0.6579
4.500 0.5754 0.01206 0.00395 -0.0401 0.0390 0.6637
4.750 0.6013 0.01228 0.00421 -0.0397 0.0378 0.6696
5.000 0.6270 0.01251 0.00449 -0.0392 0.0366 0.6761
5.250 0.6525 0.01277 0.00478 -0.0387 0.0355 0.6831
5.500 0.6777 0.01305 0.00510 -0.0382 0.0345 0.6899
5.750 0.7026 0.01337 0.00545 -0.0376 0.0334 0.6972
6.000 0.7266 0.01380 0.00591 -0.0368 0.0323 0.7042
6.250 0.7512 0.01414 0.00630 -0.0362 0.0316 0.7119
6.500 0.7759 0.01445 0.00669 -0.0356 0.0310 0.7194
6.750 0.8003 0.01481 0.00711 -0.0349 0.0305 0.7277
7.000 0.8244 0.01519 0.00755 -0.0342 0.0299 0.7360
7.250 0.8482 0.01559 0.00802 -0.0334 0.0293 0.7456
7.500 0.8718 0.01599 0.00850 -0.0326 0.0287 0.7553
7.750 0.8952 0.01641 0.00900 -0.0318 0.0282 0.7658
8.000 0.9183 0.01685 0.00951 -0.0310 0.0278 0.7776
8.250 0.9409 0.01732 0.01007 -0.0301 0.0273 0.7903
8.500 0.9627 0.01788 0.01071 -0.0290 0.0268 0.8047
8.750 0.9826 0.01873 0.01166 -0.0277 0.0261 0.8217
9.000 1.0039 0.01918 0.01225 -0.0266 0.0258 0.8438
9.250 1.0238 0.01962 0.01287 -0.0251 0.0255 0.8757
9.500 1.0446 0.02007 0.01354 -0.0237 0.0252 0.9394
9.750 1.0702 0.02078 0.01435 -0.0237 0.0248 1.0000
10.000 1.0917 0.02151 0.01518 -0.0227 0.0244 1.0000
10.250 1.1127 0.02228 0.01604 -0.0218 0.0240 1.0000
10.500 1.1331 0.02308 0.01694 -0.0208 0.0236 1.0000
10.750 1.1530 0.02386 0.01780 -0.0197 0.0233 1.0000
11.000 1.1727 0.02453 0.01854 -0.0186 0.0228 1.0000
11.250 1.1918 0.02516 0.01923 -0.0174 0.0224 1.0000
11.500 1.2105 0.02574 0.01986 -0.0162 0.0221 1.0000
11.750 1.2280 0.02637 0.02053 -0.0149 0.0217 1.0000
12.000 1.2427 0.02738 0.02161 -0.0132 0.0213 1.0000
12.250 1.2538 0.02872 0.02307 -0.0112 0.0210 1.0000
12.500 1.2653 0.02967 0.02416 -0.0090 0.0208 1.0000
12.750 1.2745 0.03077 0.02542 -0.0066 0.0206 1.0000
13.000 1.2819 0.03201 0.02682 -0.0042 0.0204 1.0000
13.250 1.2870 0.03340 0.02839 -0.0016 0.0201 1.0000
13.500 1.2904 0.03493 0.03009 0.0008 0.0199 1.0000
13.750 1.2914 0.03666 0.03199 0.0032 0.0197 1.0000
14.000 1.2910 0.03852 0.03401 0.0054 0.0194 1.0000
14.250 1.2884 0.04065 0.03632 0.0073 0.0192 1.0000
14.500 1.2852 0.04291 0.03873 0.0088 0.0190 1.0000
14.750 1.2780 0.04574 0.04173 0.0099 0.0189 1.0000
15.250 1.2575 0.05278 0.04912 0.0101 0.0186 1.0000
15.500 1.2405 0.05770 0.05423 0.0087 0.0185 1.0000
15.750 1.2192 0.06400 0.06073 0.0056 0.0185 1.0000
16.000 1.1835 0.07407 0.07106 -0.0011 0.0185 1.0000
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