N-14 (n14-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-14 (n14-il) Reynolds number: 200,000 Max Cl/Cd: 44.53 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n14-il-200000-n5.txt Download as CSV file: xf-n14-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8625 0.09860 0.09428 -0.0312 1.0000 0.0239
-15.500 -0.9011 0.08670 0.08219 -0.0388 1.0000 0.0237
-15.250 -0.9303 0.07744 0.07273 -0.0447 1.0000 0.0236
-15.000 -0.9561 0.06959 0.06465 -0.0497 1.0000 0.0237
-14.750 -0.9775 0.06320 0.05803 -0.0531 1.0000 0.0238
-14.500 -0.9945 0.05807 0.05268 -0.0552 1.0000 0.0239
-14.250 -1.0111 0.05360 0.04792 -0.0565 1.0000 0.0242
-14.000 -1.0195 0.05025 0.04446 -0.0565 1.0000 0.0245
-13.750 -1.0230 0.04771 0.04183 -0.0561 1.0000 0.0248
-13.500 -1.0242 0.04565 0.03970 -0.0553 1.0000 0.0253
-13.250 -1.0259 0.04361 0.03757 -0.0542 1.0000 0.0258
-13.000 -1.0271 0.04175 0.03558 -0.0527 1.0000 0.0263
-12.750 -1.0282 0.03996 0.03365 -0.0508 1.0000 0.0269
-12.500 -1.0283 0.03844 0.03196 -0.0486 1.0000 0.0277
-12.250 -1.0284 0.03690 0.03022 -0.0460 1.0000 0.0285
-12.000 -1.0273 0.03547 0.02857 -0.0432 1.0000 0.0292
-11.750 -1.0251 0.03428 0.02716 -0.0401 1.0000 0.0299
-11.500 -1.0203 0.03282 0.02557 -0.0374 1.0000 0.0305
-11.250 -1.0138 0.03164 0.02436 -0.0347 1.0000 0.0313
-11.000 -1.0076 0.03078 0.02346 -0.0317 1.0000 0.0322
-10.750 -1.0006 0.02994 0.02256 -0.0287 1.0000 0.0331
-10.500 -0.9910 0.02902 0.02154 -0.0260 1.0000 0.0340
-10.250 -0.9800 0.02812 0.02050 -0.0235 1.0000 0.0351
-10.000 -0.9679 0.02728 0.01952 -0.0211 1.0000 0.0361
-9.750 -0.9551 0.02652 0.01861 -0.0187 1.0000 0.0370
-9.500 -0.9426 0.02546 0.01749 -0.0164 1.0000 0.0380
-9.250 -0.9308 0.02447 0.01649 -0.0140 1.0000 0.0390
-9.000 -0.9182 0.02370 0.01567 -0.0116 1.0000 0.0401
-8.750 -0.9051 0.02299 0.01490 -0.0091 1.0000 0.0412
-8.500 -0.8916 0.02233 0.01418 -0.0067 1.0000 0.0425
-8.250 -0.8780 0.02169 0.01347 -0.0043 1.0000 0.0436
-8.000 -0.8643 0.02108 0.01278 -0.0018 1.0000 0.0446
-7.750 -0.8505 0.02052 0.01214 0.0007 1.0000 0.0454
-7.500 -0.8370 0.01998 0.01152 0.0032 1.0000 0.0463
-7.250 -0.8261 0.01927 0.01081 0.0061 1.0000 0.0480
-7.000 -0.8136 0.01873 0.01024 0.0088 1.0000 0.0496
-6.750 -0.8003 0.01827 0.00974 0.0114 1.0000 0.0514
-6.500 -0.7722 0.01776 0.00916 0.0109 0.9973 0.0537
-6.250 -0.7410 0.01728 0.00861 0.0098 0.9939 0.0564
-6.000 -0.7121 0.01673 0.00810 0.0091 0.9898 0.0615
-5.750 -0.6814 0.01625 0.00777 0.0081 0.9860 0.0737
-5.500 -0.6499 0.01595 0.00751 0.0070 0.9824 0.0951
-5.250 -0.6201 0.01566 0.00718 0.0064 0.9776 0.1069
-5.000 -0.5875 0.01540 0.00686 0.0051 0.9741 0.1162
-4.750 -0.5592 0.01502 0.00650 0.0048 0.9691 0.1243
-4.500 -0.5289 0.01475 0.00620 0.0040 0.9643 0.1314
-4.250 -0.4965 0.01436 0.00588 0.0028 0.9609 0.1437
-3.750 -0.4413 0.01358 0.00535 0.0024 0.9499 0.1907
-3.500 -0.4102 0.01308 0.00511 0.0013 0.9467 0.2434
-3.250 -0.3877 0.01265 0.00490 0.0022 0.9396 0.2942
-3.000 -0.3593 0.01221 0.00467 0.0019 0.9350 0.3425
-2.750 -0.3281 0.01179 0.00445 0.0010 0.9319 0.3895
-2.500 -0.3053 0.01143 0.00428 0.0019 0.9245 0.4360
-2.250 -0.2769 0.01095 0.00410 0.0018 0.9189 0.5042
-2.000 -0.2491 0.01052 0.00397 0.0019 0.9127 0.5734
-1.750 -0.2223 0.01021 0.00388 0.0024 0.9045 0.6318
-1.500 -0.1883 0.00996 0.00381 0.0015 0.8986 0.6801
-1.250 -0.1601 0.00983 0.00379 0.0018 0.8896 0.7154
-1.000 -0.1242 0.00970 0.00373 0.0005 0.8827 0.7469
-0.750 -0.0937 0.00963 0.00370 0.0004 0.8721 0.7733
-0.500 -0.0604 0.00957 0.00367 -0.0004 0.8607 0.7927
-0.250 -0.0250 0.00953 0.00365 -0.0016 0.8512 0.8111
0.000 0.0060 0.00954 0.00368 -0.0019 0.8412 0.8271
0.250 0.0384 0.00957 0.00372 -0.0025 0.8310 0.8414
0.500 0.0728 0.00961 0.00377 -0.0035 0.8212 0.8556
0.750 0.1068 0.00971 0.00391 -0.0043 0.8087 0.8720
1.000 0.1429 0.00984 0.00404 -0.0055 0.7917 0.8872
1.250 0.1726 0.00994 0.00410 -0.0054 0.7708 0.8993
1.500 0.2101 0.01006 0.00417 -0.0069 0.7424 0.9043
1.750 0.2395 0.01018 0.00420 -0.0068 0.7052 0.9123
2.000 0.2713 0.01036 0.00421 -0.0072 0.6567 0.9179
2.250 0.3037 0.01066 0.00427 -0.0079 0.5990 0.9228
2.500 0.3253 0.01102 0.00436 -0.0064 0.5366 0.9313
2.750 0.3537 0.01157 0.00451 -0.0065 0.4515 0.9347
3.000 0.3803 0.01204 0.00470 -0.0064 0.3945 0.9393
3.250 0.4024 0.01236 0.00487 -0.0054 0.3611 0.9464
3.500 0.4345 0.01272 0.00509 -0.0064 0.3279 0.9493
3.750 0.4647 0.01303 0.00531 -0.0071 0.3008 0.9533
4.000 0.4888 0.01329 0.00551 -0.0065 0.2763 0.9600
4.250 0.5213 0.01362 0.00573 -0.0077 0.2397 0.9628
4.500 0.5507 0.01403 0.00595 -0.0084 0.1965 0.9668
5.000 0.6067 0.01490 0.00655 -0.0092 0.1388 0.9758
5.250 0.6359 0.01534 0.00691 -0.0099 0.1176 0.9798
5.500 0.6636 0.01576 0.00728 -0.0102 0.0972 0.9844
5.750 0.6947 0.01621 0.00764 -0.0112 0.0789 0.9875
6.000 0.7244 0.01667 0.00807 -0.0120 0.0707 0.9913
6.250 0.7535 0.01719 0.00856 -0.0127 0.0658 0.9949
6.500 0.7839 0.01767 0.00910 -0.0137 0.0624 0.9982
6.750 0.8077 0.01814 0.00964 -0.0132 0.0595 1.0000
7.000 0.8211 0.01859 0.01012 -0.0107 0.0572 1.0000
7.250 0.8331 0.01915 0.01070 -0.0079 0.0553 1.0000
7.500 0.8433 0.01989 0.01143 -0.0049 0.0533 1.0000
7.750 0.8575 0.02032 0.01196 -0.0024 0.0520 1.0000
8.000 0.8714 0.02082 0.01254 0.0000 0.0503 1.0000
8.250 0.8848 0.02137 0.01316 0.0026 0.0484 1.0000
8.500 0.8978 0.02195 0.01379 0.0051 0.0465 1.0000
8.750 0.9098 0.02261 0.01447 0.0077 0.0448 1.0000
9.000 0.9200 0.02363 0.01547 0.0105 0.0431 1.0000
9.250 0.9343 0.02414 0.01612 0.0128 0.0418 1.0000
9.500 0.9476 0.02476 0.01687 0.0152 0.0401 1.0000
9.750 0.9601 0.02539 0.01759 0.0176 0.0384 1.0000
10.000 0.9716 0.02607 0.01831 0.0202 0.0370 1.0000
10.250 0.9815 0.02684 0.01909 0.0228 0.0356 1.0000
10.500 0.9906 0.02770 0.02005 0.0257 0.0344 1.0000
10.750 0.9988 0.02842 0.02093 0.0287 0.0329 1.0000
11.000 1.0062 0.02924 0.02187 0.0318 0.0316 1.0000
11.250 1.0131 0.02999 0.02270 0.0347 0.0304 1.0000
11.500 1.0196 0.03076 0.02352 0.0375 0.0295 1.0000
11.750 1.0251 0.03179 0.02457 0.0401 0.0286 1.0000
12.000 1.0308 0.03294 0.02594 0.0426 0.0274 1.0000
12.250 1.0353 0.03429 0.02746 0.0450 0.0264 1.0000
12.500 1.0392 0.03556 0.02886 0.0471 0.0253 1.0000
12.750 1.0428 0.03690 0.03031 0.0491 0.0246 1.0000
13.000 1.0451 0.03838 0.03189 0.0508 0.0239 1.0000
13.250 1.0468 0.03998 0.03356 0.0522 0.0234 1.0000
13.500 1.0458 0.04203 0.03574 0.0534 0.0229 1.0000
13.750 1.0409 0.04474 0.03869 0.0544 0.0223 1.0000
14.000 1.0349 0.04765 0.04182 0.0549 0.0216 1.0000
14.250 1.0270 0.05098 0.04536 0.0548 0.0212 1.0000
14.500 1.0181 0.05466 0.04921 0.0540 0.0207 1.0000
14.750 1.0086 0.05874 0.05346 0.0525 0.0203 1.0000
15.000 0.9933 0.06402 0.05893 0.0502 0.0202 1.0000
15.250 0.9766 0.07002 0.06512 0.0469 0.0201 1.0000
15.500 0.9571 0.07698 0.07226 0.0427 0.0199 1.0000
15.750 0.9238 0.08712 0.08264 0.0365 0.0200 1.0000
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