NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Reynolds number: 200,000 Max Cl/Cd: 36.17 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf415-il-200000.txt Download as CSV file: xf-nlf415-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF(2)-0415 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3666 0.10017 0.09652 -0.1058 0.9612 0.0515
-11.250 -0.3842 0.09337 0.08967 -0.1116 0.9597 0.0518
-11.000 -0.4137 0.09183 0.08816 -0.1067 0.9557 0.0517
-10.750 -0.4377 0.08869 0.08500 -0.1057 0.9534 0.0517
-10.500 -0.4632 0.08565 0.08192 -0.1047 0.9515 0.0517
-10.250 -0.4887 0.08303 0.07924 -0.1032 0.9499 0.0517
-10.000 -0.5141 0.08052 0.07663 -0.1022 0.9481 0.0518
-9.750 -0.5398 0.07898 0.07504 -0.0987 0.9472 0.0518
-9.500 -0.5683 0.07804 0.07406 -0.0933 0.9466 0.0517
-9.250 -0.5942 0.07694 0.07295 -0.0872 0.9467 0.0516
-9.000 -0.7178 0.08853 0.08539 -0.0392 1.0000 0.0448
-8.750 -0.7709 0.08533 0.08207 -0.0356 1.0000 0.0434
-8.500 -0.7957 0.08217 0.07879 -0.0332 1.0000 0.0433
-8.250 -0.8044 0.07924 0.07580 -0.0313 1.0000 0.0442
-8.000 -0.8119 0.07629 0.07277 -0.0295 1.0000 0.0453
-7.750 -0.8185 0.07305 0.06939 -0.0279 1.0000 0.0465
-7.500 -0.8209 0.06977 0.06591 -0.0266 0.9998 0.0483
-7.250 -0.8141 0.07062 0.06593 -0.0257 0.9973 0.0525
-7.000 -0.8116 0.06159 0.05681 -0.0269 0.9960 0.0542
-6.750 -0.7952 0.05810 0.05336 -0.0276 0.9948 0.0561
-6.500 -0.7821 0.05547 0.05061 -0.0272 0.9942 0.0586
-6.250 -0.7615 0.05822 0.05253 -0.0258 0.9916 0.0657
-6.000 -0.7510 0.04960 0.04405 -0.0269 0.9908 0.0689
-5.750 -0.7295 0.04734 0.04172 -0.0275 0.9889 0.0730
-5.500 -0.7070 0.04491 0.03892 -0.0284 0.9872 0.0833
-5.250 -0.6826 0.04360 0.03726 -0.0293 0.9859 0.0958
-5.000 -0.6590 0.04177 0.03530 -0.0302 0.9850 0.1104
-4.750 -0.6397 0.03968 0.03323 -0.0305 0.9845 0.1267
-4.500 -0.5992 0.03535 0.02791 -0.0259 0.9839 0.0577
-4.250 -0.5707 0.03382 0.02578 -0.0233 0.9814 0.0412
-4.000 -0.5466 0.03182 0.02376 -0.0226 0.9801 0.0395
-3.750 -0.5215 0.03065 0.02250 -0.0221 0.9785 0.0389
-3.500 -0.4954 0.02992 0.02171 -0.0219 0.9769 0.0390
-3.250 -0.4671 0.02970 0.02140 -0.0224 0.9753 0.0403
-3.000 -0.4393 0.02945 0.02113 -0.0228 0.9742 0.0406
-2.750 -0.4114 0.02930 0.02097 -0.0234 0.9734 0.0408
-2.500 -0.3846 0.02885 0.02052 -0.0241 0.9728 0.0421
-2.250 -0.3696 0.02734 0.01898 -0.0227 0.9687 0.0442
-2.000 -0.3416 0.02712 0.01868 -0.0236 0.9658 0.0475
-1.500 -0.2839 0.02557 0.01911 -0.0270 0.9632 0.5848
-1.250 -0.2569 0.02835 0.02209 -0.0251 0.9606 0.6438
-1.000 -0.2479 0.02857 0.02237 -0.0211 0.9557 0.6644
-0.750 -0.2248 0.02945 0.02329 -0.0197 0.9510 0.6787
-0.500 -0.1992 0.03063 0.02451 -0.0187 0.9485 0.6911
-0.250 -0.1723 0.03254 0.02644 -0.0178 0.9468 0.7112
0.000 -0.1648 0.03152 0.02543 -0.0145 0.9395 0.7134
0.250 -0.1348 0.03195 0.02581 -0.0157 0.9362 0.7151
0.500 -0.0996 0.03264 0.02641 -0.0182 0.9341 0.7152
0.750 -0.0631 0.03382 0.02752 -0.0210 0.9328 0.7154
1.000 -0.0542 0.03265 0.02632 -0.0185 0.9239 0.7160
1.250 -0.0208 0.03323 0.02685 -0.0205 0.9209 0.7168
1.500 0.0169 0.03428 0.02786 -0.0234 0.9189 0.7173
1.750 0.0285 0.03367 0.02724 -0.0215 0.9101 0.7178
2.000 0.0642 0.03427 0.02782 -0.0239 0.9062 0.7183
2.250 0.1058 0.03549 0.02904 -0.0274 0.9040 0.7189
2.500 0.1201 0.03485 0.02839 -0.0259 0.8927 0.7195
2.750 0.1506 0.03520 0.02875 -0.0272 0.8841 0.7201
3.000 0.2078 0.03485 0.02841 -0.0320 0.8634 0.7209
3.250 0.2459 0.03475 0.02833 -0.0340 0.8511 0.7217
3.500 0.2905 0.03500 0.02863 -0.0374 0.8465 0.7230
3.750 0.3187 0.03480 0.02847 -0.0378 0.8348 0.7241
4.000 0.3835 0.03353 0.02727 -0.0430 0.8190 0.7251
4.250 0.4572 0.03132 0.02516 -0.0490 0.8036 0.7260
4.500 0.5012 0.03003 0.02397 -0.0509 0.7922 0.7269
4.750 0.5689 0.02809 0.02222 -0.0565 0.7876 0.7279
5.000 0.5979 0.02717 0.02142 -0.0561 0.7760 0.7291
5.250 0.6367 0.02568 0.02009 -0.0570 0.7643 0.7303
5.500 0.6756 0.02384 0.01841 -0.0575 0.7487 0.7317
5.750 0.6896 0.02318 0.01786 -0.0546 0.7250 0.7331
6.000 0.6955 0.02302 0.01779 -0.0507 0.6849 0.7347
6.250 0.7418 0.02051 0.01258 -0.0494 0.2381 0.7360
6.500 0.7462 0.02185 0.01345 -0.0463 0.1721 0.7377
6.750 0.7584 0.02286 0.01423 -0.0444 0.1412 0.7396
7.000 0.7738 0.02365 0.01497 -0.0429 0.1218 0.7413
7.250 0.7903 0.02444 0.01573 -0.0415 0.1086 0.7429
7.500 0.8081 0.02528 0.01651 -0.0404 0.0980 0.7446
7.750 0.8290 0.02590 0.01720 -0.0397 0.0899 0.7465
8.000 0.8525 0.02678 0.01806 -0.0393 0.0831 0.7485
8.250 0.8754 0.02741 0.01875 -0.0390 0.0765 0.7508
8.500 0.9041 0.02834 0.01970 -0.0395 0.0701 0.7531
8.750 0.9225 0.02887 0.02030 -0.0386 0.0636 0.7555
9.000 0.9451 0.02970 0.02121 -0.0383 0.0567 0.7577
9.250 0.9627 0.03032 0.02190 -0.0373 0.0510 0.7602
9.500 0.9853 0.03135 0.02308 -0.0369 0.0441 0.7631
9.750 1.0149 0.03294 0.02466 -0.0377 0.0376 0.7662
10.000 1.0392 0.03413 0.02610 -0.0373 0.0337 0.7696
10.250 1.0610 0.03536 0.02740 -0.0369 0.0309 0.7728
10.500 1.0913 0.03783 0.03019 -0.0375 0.0282 0.7765
10.750 1.1097 0.03962 0.03232 -0.0365 0.0263 0.7807
11.000 1.1274 0.04180 0.03479 -0.0355 0.0253 0.7851
11.250 1.1392 0.04408 0.03738 -0.0338 0.0245 0.7891
11.500 1.1464 0.04665 0.04027 -0.0316 0.0241 0.7939
11.750 1.1491 0.04954 0.04345 -0.0291 0.0237 0.7991
12.000 1.1452 0.05278 0.04707 -0.0260 0.0236 0.8038
12.250 1.1335 0.05665 0.05135 -0.0223 0.0237 0.8091
12.500 1.1136 0.06118 0.05631 -0.0183 0.0239 0.8146
12.750 1.0586 0.06964 0.06546 -0.0126 0.0251 0.8168
13.000 1.0221 0.07621 0.07240 -0.0100 0.0259 0.8208
13.250 0.9908 0.08240 0.07886 -0.0091 0.0263 0.8262
13.500 0.9594 0.08906 0.08576 -0.0095 0.0267 0.8320
13.750 0.9287 0.09650 0.09340 -0.0118 0.0272 0.8390
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