N-14 (n14-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-14 (n14-il) Reynolds number: 500,000 Max Cl/Cd: 56.1 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n14-il-500000.txt Download as CSV file: xf-n14-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: N-14
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9901 0.08438 0.08106 -0.0401 1.0000 0.0195
-16.250 -1.0146 0.07615 0.07266 -0.0453 1.0000 0.0195
-16.000 -1.0359 0.06911 0.06546 -0.0495 1.0000 0.0196
-15.750 -1.0496 0.06373 0.05995 -0.0524 1.0000 0.0198
-15.500 -1.0577 0.05954 0.05567 -0.0544 1.0000 0.0200
-15.250 -1.0634 0.05595 0.05200 -0.0559 1.0000 0.0202
-15.000 -1.0754 0.05174 0.04763 -0.0572 1.0000 0.0203
-14.750 -1.0779 0.04911 0.04493 -0.0577 1.0000 0.0206
-14.500 -1.0844 0.04614 0.04182 -0.0577 1.0000 0.0209
-14.250 -1.0881 0.04374 0.03931 -0.0572 1.0000 0.0212
-14.000 -1.0912 0.04150 0.03693 -0.0562 1.0000 0.0215
-13.750 -1.0928 0.03962 0.03493 -0.0549 1.0000 0.0220
-13.500 -1.0955 0.03773 0.03288 -0.0531 1.0000 0.0224
-13.250 -1.0974 0.03608 0.03106 -0.0508 1.0000 0.0229
-13.000 -1.0976 0.03493 0.02974 -0.0483 1.0000 0.0233
-12.750 -1.0973 0.03378 0.02844 -0.0454 1.0000 0.0235
-12.500 -1.0982 0.03117 0.02567 -0.0426 1.0000 0.0242
-12.250 -1.0918 0.03009 0.02458 -0.0401 1.0000 0.0247
-12.000 -1.0858 0.02918 0.02361 -0.0372 1.0000 0.0252
-11.750 -1.0805 0.02848 0.02284 -0.0340 1.0000 0.0257
-11.500 -1.0759 0.02776 0.02204 -0.0304 1.0000 0.0263
-11.250 -1.0702 0.02707 0.02126 -0.0269 1.0000 0.0269
-11.000 -1.0609 0.02633 0.02042 -0.0239 1.0000 0.0276
-10.750 -1.0510 0.02589 0.01986 -0.0210 1.0000 0.0284
-10.500 -1.0404 0.02513 0.01897 -0.0182 1.0000 0.0289
-10.250 -1.0283 0.02328 0.01706 -0.0161 1.0000 0.0299
-10.000 -1.0158 0.02253 0.01630 -0.0137 1.0000 0.0306
-9.750 -1.0026 0.02198 0.01572 -0.0112 1.0000 0.0315
-9.500 -0.9891 0.02140 0.01509 -0.0088 1.0000 0.0324
-9.250 -0.9751 0.02086 0.01449 -0.0064 1.0000 0.0334
-9.000 -0.9608 0.02033 0.01388 -0.0039 1.0000 0.0341
-8.750 -0.9461 0.01992 0.01339 -0.0016 1.0000 0.0347
-8.500 -0.9348 0.01885 0.01225 0.0013 1.0000 0.0356
-8.250 -0.9245 0.01797 0.01137 0.0043 1.0000 0.0367
-8.000 -0.9120 0.01748 0.01086 0.0070 1.0000 0.0378
-7.750 -0.8995 0.01703 0.01038 0.0097 1.0000 0.0387
-7.500 -0.8871 0.01661 0.00992 0.0125 1.0000 0.0396
-7.250 -0.8605 0.01614 0.00940 0.0124 0.9986 0.0409
-7.000 -0.8268 0.01576 0.00896 0.0109 0.9961 0.0420
-6.750 -0.7958 0.01493 0.00809 0.0097 0.9936 0.0439
-6.500 -0.7660 0.01431 0.00746 0.0089 0.9901 0.0457
-6.250 -0.7336 0.01386 0.00699 0.0076 0.9870 0.0479
-6.000 -0.6992 0.01347 0.00655 0.0060 0.9847 0.0502
-5.750 -0.6650 0.01297 0.00605 0.0044 0.9827 0.0542
-5.500 -0.6372 0.01252 0.00561 0.0042 0.9775 0.0593
-5.250 -0.6048 0.01203 0.00536 0.0030 0.9742 0.0908
-5.000 -0.5684 0.01184 0.00520 0.0010 0.9721 0.1099
-4.750 -0.5323 0.01153 0.00494 -0.0009 0.9705 0.1207
-4.500 -0.5061 0.01128 0.00468 -0.0007 0.9643 0.1277
-4.250 -0.4729 0.01100 0.00442 -0.0019 0.9612 0.1351
-4.000 -0.4378 0.01071 0.00417 -0.0036 0.9591 0.1435
-3.750 -0.4016 0.01036 0.00391 -0.0055 0.9574 0.1587
-3.500 -0.3745 0.00990 0.00366 -0.0055 0.9515 0.2001
-3.250 -0.3422 0.00937 0.00339 -0.0067 0.9472 0.2609
-3.000 -0.3069 0.00889 0.00314 -0.0084 0.9443 0.3147
-2.750 -0.2764 0.00838 0.00290 -0.0092 0.9394 0.3781
-2.500 -0.2531 0.00782 0.00268 -0.0083 0.9318 0.4610
-2.250 -0.2261 0.00719 0.00248 -0.0082 0.9269 0.5646
-2.000 -0.2063 0.00685 0.00239 -0.0063 0.9173 0.6293
-1.750 -0.1758 0.00659 0.00227 -0.0067 0.9112 0.6784
-1.500 -0.1532 0.00644 0.00224 -0.0053 0.9005 0.7158
-1.250 -0.1255 0.00633 0.00220 -0.0049 0.8916 0.7492
-1.000 -0.0986 0.00626 0.00218 -0.0044 0.8825 0.7725
-0.750 -0.0719 0.00623 0.00217 -0.0038 0.8741 0.7914
-0.500 -0.0440 0.00621 0.00216 -0.0036 0.8655 0.8075
-0.250 -0.0181 0.00620 0.00217 -0.0029 0.8554 0.8217
0.000 0.0097 0.00620 0.00216 -0.0025 0.8452 0.8350
0.250 0.0358 0.00621 0.00216 -0.0018 0.8329 0.8484
0.500 0.0617 0.00622 0.00218 -0.0011 0.8192 0.8606
0.750 0.0897 0.00624 0.00221 -0.0008 0.8057 0.8705
1.000 0.1158 0.00628 0.00223 -0.0001 0.7921 0.8810
1.250 0.1434 0.00632 0.00227 0.0003 0.7763 0.8908
1.500 0.1721 0.00639 0.00231 0.0004 0.7549 0.9006
1.750 0.1984 0.00650 0.00238 0.0012 0.7283 0.9125
2.000 0.2268 0.00672 0.00248 0.0015 0.6874 0.9230
2.250 0.2562 0.00702 0.00260 0.0015 0.6348 0.9303
2.500 0.2834 0.00743 0.00277 0.0019 0.5733 0.9370
2.750 0.3086 0.00789 0.00295 0.0025 0.5014 0.9434
3.000 0.3411 0.00844 0.00318 0.0014 0.4260 0.9462
3.250 0.3746 0.00890 0.00343 0.0001 0.3772 0.9497
3.500 0.3992 0.00925 0.00364 0.0007 0.3446 0.9566
3.750 0.4386 0.00962 0.00389 -0.0018 0.3145 0.9584
4.000 0.4742 0.00992 0.00410 -0.0036 0.2870 0.9604
4.250 0.5072 0.01022 0.00427 -0.0049 0.2528 0.9632
4.500 0.5335 0.01059 0.00446 -0.0047 0.2090 0.9684
4.750 0.5632 0.01106 0.00471 -0.0055 0.1641 0.9716
5.000 0.5967 0.01152 0.00500 -0.0070 0.1309 0.9736
5.250 0.6282 0.01204 0.00533 -0.0081 0.0941 0.9766
5.500 0.6567 0.01253 0.00567 -0.0085 0.0718 0.9807
5.750 0.6874 0.01292 0.00603 -0.0093 0.0654 0.9839
6.000 0.7208 0.01339 0.00649 -0.0108 0.0601 0.9860
6.250 0.7538 0.01375 0.00690 -0.0121 0.0572 0.9886
6.500 0.7846 0.01421 0.00736 -0.0131 0.0541 0.9917
6.750 0.8128 0.01502 0.00818 -0.0136 0.0507 0.9947
7.000 0.8469 0.01530 0.00853 -0.0152 0.0489 0.9969
7.250 0.8797 0.01568 0.00895 -0.0166 0.0464 0.9992
7.500 0.9007 0.01610 0.00938 -0.0156 0.0445 1.0000
7.750 0.9097 0.01681 0.01009 -0.0123 0.0427 1.0000
8.000 0.9216 0.01732 0.01066 -0.0094 0.0414 1.0000
8.250 0.9359 0.01760 0.01101 -0.0069 0.0401 1.0000
8.500 0.9494 0.01796 0.01141 -0.0043 0.0388 1.0000
8.750 0.9631 0.01830 0.01177 -0.0018 0.0372 1.0000
9.000 0.9751 0.01879 0.01225 0.0010 0.0359 1.0000
9.250 0.9834 0.01978 0.01328 0.0043 0.0344 1.0000
9.500 0.9977 0.02010 0.01369 0.0068 0.0334 1.0000
9.750 1.0111 0.02052 0.01418 0.0093 0.0322 1.0000
10.000 1.0244 0.02089 0.01458 0.0119 0.0310 1.0000
10.250 1.0364 0.02137 0.01507 0.0145 0.0300 1.0000
10.500 1.0430 0.02258 0.01629 0.0178 0.0286 1.0000
10.750 1.0546 0.02289 0.01670 0.0207 0.0278 1.0000
11.000 1.0624 0.02340 0.01731 0.0241 0.0270 1.0000
11.250 1.0700 0.02389 0.01786 0.0275 0.0261 1.0000
11.500 1.0781 0.02447 0.01848 0.0306 0.0254 1.0000
11.750 1.0867 0.02506 0.01910 0.0334 0.0247 1.0000
12.000 1.0928 0.02605 0.02013 0.0363 0.0240 1.0000
12.250 1.0973 0.02740 0.02159 0.0392 0.0233 1.0000
12.500 1.1052 0.02823 0.02256 0.0416 0.0227 1.0000
12.750 1.1117 0.02930 0.02374 0.0439 0.0221 1.0000
13.000 1.1186 0.03027 0.02480 0.0460 0.0214 1.0000
13.250 1.1264 0.03115 0.02574 0.0477 0.0208 1.0000
13.500 1.1324 0.03233 0.02697 0.0494 0.0203 1.0000
13.750 1.1361 0.03380 0.02851 0.0510 0.0200 1.0000
14.000 1.1348 0.03593 0.03073 0.0526 0.0195 1.0000
14.250 1.1305 0.03846 0.03342 0.0541 0.0192 1.0000
14.500 1.1284 0.04081 0.03595 0.0550 0.0190 1.0000
14.750 1.1259 0.04331 0.03861 0.0554 0.0186 1.0000
15.000 1.1203 0.04638 0.04184 0.0555 0.0185 1.0000
15.250 1.1158 0.04946 0.04508 0.0550 0.0180 1.0000
15.500 1.1054 0.05358 0.04936 0.0539 0.0179 1.0000
15.750 1.0957 0.05788 0.05382 0.0522 0.0177 1.0000
16.000 1.0838 0.06282 0.05892 0.0498 0.0175 1.0000
16.250 1.0695 0.06850 0.06476 0.0467 0.0174 1.0000
16.500 1.0487 0.07562 0.07206 0.0427 0.0174 1.0000
16.750 1.0302 0.08275 0.07934 0.0384 0.0173 1.0000
17.000 0.9966 0.09288 0.08968 0.0324 0.0174 1.0000
17.250 0.9338 0.10954 0.10665 0.0225 0.0179 1.0000
17.500 0.6707 0.18978 0.18715 -0.0136 0.0243 1.0000
17.750 0.6805 0.19185 0.18922 -0.0140 0.0240 1.0000
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Polar data table (+)
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