NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Reynolds number: 200,000 Max Cl/Cd: 38.16 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nplx-il-200000-n5.txt Download as CSV file: xf-nplx-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6272 0.09226 0.08814 -0.0309 1.0000 0.0156
-10.750 -0.6713 0.07516 0.07101 -0.0418 1.0000 0.0151
-10.500 -0.7200 0.06303 0.05867 -0.0488 1.0000 0.0148
-10.250 -0.7572 0.05556 0.05096 -0.0514 1.0000 0.0146
-10.000 -0.7888 0.05017 0.04533 -0.0512 1.0000 0.0145
-9.750 -0.8172 0.04626 0.04118 -0.0483 1.0000 0.0144
-9.500 -0.8339 0.04239 0.03699 -0.0454 1.0000 0.0145
-9.250 -0.8423 0.03876 0.03300 -0.0428 1.0000 0.0146
-9.000 -0.8425 0.03575 0.02964 -0.0404 1.0000 0.0148
-8.750 -0.8376 0.03309 0.02665 -0.0383 1.0000 0.0149
-8.500 -0.8286 0.03079 0.02405 -0.0364 1.0000 0.0152
-8.250 -0.8167 0.02881 0.02178 -0.0346 1.0000 0.0155
-8.000 -0.8028 0.02706 0.01977 -0.0329 1.0000 0.0159
-7.750 -0.7875 0.02554 0.01801 -0.0312 1.0000 0.0162
-7.500 -0.7714 0.02425 0.01659 -0.0297 1.0000 0.0166
-7.250 -0.7546 0.02334 0.01563 -0.0283 1.0000 0.0170
-7.000 -0.7367 0.02268 0.01494 -0.0270 1.0000 0.0178
-6.750 -0.7187 0.02192 0.01410 -0.0256 1.0000 0.0187
-6.500 -0.7006 0.02106 0.01311 -0.0242 1.0000 0.0198
-6.250 -0.6828 0.02022 0.01221 -0.0228 1.0000 0.0208
-6.000 -0.6644 0.01958 0.01157 -0.0215 1.0000 0.0218
-5.750 -0.6441 0.01888 0.01082 -0.0205 0.9997 0.0235
-5.500 -0.6129 0.01805 0.00992 -0.0218 0.9968 0.0257
-5.250 -0.5805 0.01747 0.00932 -0.0233 0.9940 0.0285
-5.000 -0.5500 0.01683 0.00864 -0.0244 0.9905 0.0318
-4.750 -0.5181 0.01641 0.00820 -0.0257 0.9871 0.0363
-4.500 -0.4856 0.01593 0.00773 -0.0272 0.9843 0.0409
-4.250 -0.4557 0.01552 0.00729 -0.0280 0.9802 0.0463
-4.000 -0.4244 0.01510 0.00690 -0.0292 0.9762 0.0532
-3.750 -0.3914 0.01462 0.00644 -0.0307 0.9732 0.0598
-3.500 -0.3618 0.01423 0.00605 -0.0314 0.9687 0.0677
-3.250 -0.3313 0.01385 0.00567 -0.0322 0.9644 0.0787
-3.000 -0.2987 0.01340 0.00529 -0.0336 0.9612 0.0963
-2.750 -0.2666 0.01291 0.00495 -0.0350 0.9579 0.1281
-2.500 -0.2394 0.01221 0.00455 -0.0355 0.9522 0.2056
-2.250 -0.2128 0.01085 0.00439 -0.0365 0.9485 0.5034
-2.000 -0.1787 0.01081 0.00439 -0.0377 0.9459 0.5411
-1.750 -0.1493 0.01079 0.00440 -0.0379 0.9409 0.5623
-1.500 -0.1185 0.01081 0.00443 -0.0383 0.9364 0.5836
-1.250 -0.0851 0.01083 0.00445 -0.0393 0.9333 0.6027
-1.000 -0.0501 0.01081 0.00446 -0.0407 0.9309 0.6136
-0.750 -0.0205 0.01079 0.00444 -0.0409 0.9249 0.6223
-0.500 0.0130 0.01074 0.00440 -0.0419 0.9197 0.6305
-0.250 0.0514 0.01062 0.00427 -0.0438 0.9152 0.6376
0.000 0.0818 0.01051 0.00419 -0.0441 0.9053 0.6416
0.250 0.1190 0.01037 0.00404 -0.0457 0.8979 0.6456
0.500 0.1501 0.01029 0.00395 -0.0461 0.8876 0.6498
0.750 0.1824 0.01018 0.00386 -0.0467 0.8754 0.6534
1.000 0.2156 0.01005 0.00375 -0.0473 0.8581 0.6569
1.250 0.2489 0.00994 0.00362 -0.0479 0.8379 0.6611
1.500 0.2791 0.00991 0.00356 -0.0480 0.8172 0.6660
1.750 0.3083 0.00990 0.00351 -0.0478 0.7894 0.6704
2.000 0.3345 0.00996 0.00344 -0.0468 0.7386 0.6750
2.250 0.3546 0.01034 0.00327 -0.0445 0.5977 0.6802
2.500 0.3657 0.01140 0.00342 -0.0411 0.4143 0.6851
2.750 0.3838 0.01215 0.00369 -0.0394 0.3029 0.6898
3.000 0.4036 0.01290 0.00395 -0.0381 0.1895 0.6953
3.250 0.4249 0.01361 0.00429 -0.0371 0.1143 0.7013
3.500 0.4488 0.01400 0.00460 -0.0363 0.0918 0.7070
3.750 0.4734 0.01435 0.00492 -0.0357 0.0783 0.7140
4.000 0.4976 0.01471 0.00525 -0.0350 0.0686 0.7204
4.250 0.5224 0.01502 0.00561 -0.0343 0.0625 0.7275
4.500 0.5462 0.01545 0.00603 -0.0336 0.0580 0.7346
4.750 0.5703 0.01580 0.00646 -0.0328 0.0551 0.7419
5.000 0.5944 0.01618 0.00689 -0.0320 0.0524 0.7499
5.250 0.6180 0.01657 0.00733 -0.0312 0.0500 0.7585
5.500 0.6403 0.01715 0.00790 -0.0302 0.0477 0.7677
5.750 0.6639 0.01757 0.00842 -0.0294 0.0462 0.7781
6.000 0.6868 0.01808 0.00903 -0.0283 0.0449 0.7887
6.250 0.7096 0.01862 0.00966 -0.0274 0.0436 0.8004
6.500 0.7322 0.01919 0.01030 -0.0264 0.0425 0.8133
6.750 0.7549 0.01978 0.01097 -0.0254 0.0416 0.8279
7.000 0.7769 0.02039 0.01165 -0.0243 0.0406 0.8453
7.250 0.7982 0.02122 0.01254 -0.0231 0.0395 0.8678
7.500 0.8202 0.02190 0.01338 -0.0219 0.0386 0.8981
7.750 0.8500 0.02269 0.01439 -0.0224 0.0376 0.9681
8.000 0.8746 0.02369 0.01550 -0.0221 0.0368 1.0000
8.250 0.8987 0.02478 0.01670 -0.0216 0.0360 1.0000
8.500 0.9220 0.02592 0.01798 -0.0211 0.0353 1.0000
8.750 0.9446 0.02713 0.01933 -0.0204 0.0347 1.0000
9.000 0.9663 0.02831 0.02063 -0.0197 0.0341 1.0000
9.250 0.9872 0.02943 0.02185 -0.0189 0.0334 1.0000
9.500 1.0075 0.03057 0.02306 -0.0182 0.0327 1.0000
9.750 1.0254 0.03248 0.02507 -0.0173 0.0320 1.0000
10.000 1.0407 0.03419 0.02713 -0.0157 0.0315 1.0000
10.250 1.0529 0.03640 0.02970 -0.0140 0.0311 1.0000
10.500 1.0611 0.03900 0.03268 -0.0119 0.0306 1.0000
10.750 1.0645 0.04197 0.03603 -0.0094 0.0301 1.0000
11.000 1.0626 0.04522 0.03966 -0.0067 0.0297 1.0000
11.250 1.0552 0.04858 0.04337 -0.0037 0.0293 1.0000
11.500 1.0412 0.05167 0.04672 -0.0001 0.0290 1.0000
11.750 1.0232 0.05502 0.05031 0.0030 0.0287 1.0000
12.000 1.0001 0.05907 0.05460 0.0049 0.0285 1.0000
12.250 0.9685 0.06467 0.06043 0.0048 0.0285 1.0000
12.500 0.9105 0.07587 0.07194 -0.0010 0.0288 1.0000
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