Falcon (falcon-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Falcon (falcon-il) Reynolds number: 200,000 Max Cl/Cd: 58.13 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-falcon-il-200000.txt Download as CSV file: xf-falcon-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: Falcon
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6743 0.07406 0.07012 -0.0450 1.0000 0.0454
-11.000 -0.6884 0.06910 0.06514 -0.0463 1.0000 0.0449
-10.750 -0.7116 0.06427 0.06021 -0.0468 1.0000 0.0444
-10.500 -0.7364 0.06018 0.05600 -0.0450 1.0000 0.0440
-10.250 -0.7613 0.05662 0.05228 -0.0411 1.0000 0.0435
-10.000 -0.7826 0.05246 0.04789 -0.0373 1.0000 0.0432
-9.750 -0.7992 0.04823 0.04335 -0.0332 1.0000 0.0429
-9.500 -0.8106 0.04413 0.03889 -0.0292 1.0000 0.0428
-9.250 -0.8164 0.04029 0.03466 -0.0252 1.0000 0.0427
-9.000 -0.8164 0.03693 0.03090 -0.0215 1.0000 0.0429
-8.750 -0.8109 0.03413 0.02773 -0.0183 1.0000 0.0434
-8.500 -0.8019 0.03180 0.02504 -0.0153 1.0000 0.0442
-8.250 -0.7904 0.03026 0.02313 -0.0125 1.0000 0.0454
-8.000 -0.7773 0.02796 0.02061 -0.0103 1.0000 0.0468
-7.750 -0.7607 0.02672 0.01937 -0.0086 1.0000 0.0483
-7.500 -0.7446 0.02564 0.01819 -0.0065 1.0000 0.0497
-7.250 -0.7284 0.02456 0.01699 -0.0044 1.0000 0.0514
-7.000 -0.7125 0.02366 0.01592 -0.0022 1.0000 0.0534
-6.750 -0.6963 0.02263 0.01473 0.0000 1.0000 0.0555
-6.500 -0.6798 0.02161 0.01376 0.0018 1.0000 0.0581
-6.250 -0.6634 0.02097 0.01311 0.0038 1.0000 0.0607
-6.000 -0.6467 0.02035 0.01240 0.0058 1.0000 0.0638
-5.750 -0.6305 0.01951 0.01154 0.0077 1.0000 0.0675
-5.500 -0.6136 0.01910 0.01117 0.0094 0.9999 0.0720
-5.250 -0.5715 0.01819 0.01025 0.0063 0.9952 0.0801
-5.000 -0.5294 0.01759 0.00962 0.0031 0.9886 0.0909
-4.750 -0.4889 0.01691 0.00898 0.0003 0.9811 0.1046
-4.500 -0.4489 0.01613 0.00831 -0.0025 0.9738 0.1213
-4.250 -0.4062 0.01541 0.00768 -0.0058 0.9678 0.1404
-4.000 -0.3663 0.01474 0.00709 -0.0084 0.9598 0.1613
-3.750 -0.3220 0.01390 0.00640 -0.0120 0.9549 0.1894
-3.500 -0.2861 0.01283 0.00574 -0.0141 0.9452 0.2521
-3.250 -0.2625 0.01132 0.00539 -0.0136 0.9330 0.5027
-3.000 -0.2328 0.01076 0.00525 -0.0135 0.9194 0.6088
-2.750 -0.2033 0.01047 0.00519 -0.0132 0.9039 0.6771
-2.500 -0.1751 0.01032 0.00516 -0.0124 0.8866 0.7287
-2.250 -0.1473 0.01024 0.00510 -0.0116 0.8683 0.7666
-2.000 -0.1193 0.01020 0.00504 -0.0108 0.8496 0.7985
-1.750 -0.0893 0.01020 0.00499 -0.0103 0.8307 0.8250
-1.500 -0.0614 0.01024 0.00497 -0.0096 0.8091 0.8491
-1.250 -0.0298 0.01033 0.00497 -0.0096 0.7880 0.8690
-1.000 0.0031 0.01047 0.00498 -0.0099 0.7675 0.8876
-0.750 0.0381 0.01066 0.00503 -0.0107 0.7467 0.9040
-0.500 0.0764 0.01089 0.00513 -0.0122 0.7255 0.9184
-0.250 0.1194 0.01120 0.00528 -0.0147 0.7050 0.9316
0.000 0.1623 0.01150 0.00541 -0.0173 0.6855 0.9429
0.250 0.2090 0.01176 0.00550 -0.0211 0.6655 0.9472
0.500 0.2444 0.01193 0.00554 -0.0225 0.6472 0.9561
0.750 0.2891 0.01212 0.00560 -0.0260 0.6284 0.9603
1.000 0.3260 0.01229 0.00565 -0.0279 0.6113 0.9683
1.250 0.3693 0.01245 0.00569 -0.0312 0.5934 0.9732
1.500 0.4087 0.01259 0.00573 -0.0337 0.5765 0.9800
1.750 0.4489 0.01274 0.00577 -0.0365 0.5598 0.9867
2.000 0.4909 0.01282 0.00577 -0.0397 0.5428 0.9927
2.250 0.5332 0.01288 0.00573 -0.0430 0.5261 0.9981
2.500 0.5633 0.01291 0.00569 -0.0439 0.5111 1.0000
2.750 0.5845 0.01295 0.00568 -0.0429 0.4979 1.0000
3.000 0.6057 0.01302 0.00567 -0.0419 0.4853 1.0000
3.250 0.6268 0.01309 0.00567 -0.0408 0.4729 1.0000
3.500 0.6479 0.01315 0.00572 -0.0398 0.4598 1.0000
3.750 0.6690 0.01324 0.00578 -0.0387 0.4475 1.0000
4.000 0.6900 0.01336 0.00585 -0.0376 0.4359 1.0000
4.250 0.7109 0.01351 0.00592 -0.0364 0.4245 1.0000
4.500 0.7313 0.01362 0.00605 -0.0351 0.4122 1.0000
4.750 0.7517 0.01378 0.00620 -0.0338 0.4009 1.0000
5.000 0.7720 0.01398 0.00634 -0.0324 0.3900 1.0000
5.250 0.7921 0.01417 0.00651 -0.0310 0.3784 1.0000
5.500 0.8123 0.01436 0.00672 -0.0297 0.3666 1.0000
5.750 0.8326 0.01461 0.00693 -0.0283 0.3555 1.0000
6.000 0.8529 0.01490 0.00715 -0.0270 0.3449 1.0000
6.250 0.8734 0.01513 0.00743 -0.0256 0.3330 1.0000
6.500 0.8939 0.01542 0.00772 -0.0243 0.3214 1.0000
6.750 0.9142 0.01576 0.00801 -0.0230 0.3102 1.0000
7.000 0.9345 0.01610 0.00832 -0.0216 0.2989 1.0000
7.250 0.9551 0.01643 0.00871 -0.0203 0.2875 1.0000
7.500 0.9755 0.01685 0.00911 -0.0191 0.2773 1.0000
7.750 0.9957 0.01730 0.00950 -0.0178 0.2675 1.0000
8.000 1.0159 0.01769 0.00998 -0.0165 0.2573 1.0000
8.250 1.0357 0.01818 0.01043 -0.0152 0.2480 1.0000
8.500 1.0550 0.01858 0.01083 -0.0137 0.2382 1.0000
8.750 1.0740 0.01898 0.01130 -0.0123 0.2283 1.0000
9.000 1.0924 0.01946 0.01175 -0.0108 0.2193 1.0000
9.250 1.1109 0.01984 0.01220 -0.0093 0.2103 1.0000
9.500 1.1288 0.02033 0.01272 -0.0078 0.2021 1.0000
9.750 1.1460 0.02077 0.01318 -0.0062 0.1939 1.0000
10.000 1.1633 0.02125 0.01374 -0.0046 0.1861 1.0000
10.250 1.1787 0.02176 0.01425 -0.0028 0.1781 1.0000
10.500 1.1952 0.02221 0.01484 -0.0012 0.1705 1.0000
10.750 1.2084 0.02280 0.01541 0.0009 0.1629 1.0000
11.000 1.2233 0.02319 0.01598 0.0028 0.1534 1.0000
11.250 1.2347 0.02372 0.01657 0.0051 0.1412 1.0000
11.500 1.2418 0.02435 0.01723 0.0081 0.1248 1.0000
11.750 1.2426 0.02549 0.01823 0.0115 0.0947 1.0000
12.000 1.2303 0.02769 0.02012 0.0158 0.0580 1.0000
12.250 1.2209 0.03001 0.02235 0.0190 0.0472 1.0000
12.500 1.2156 0.03230 0.02469 0.0213 0.0428 1.0000
12.750 1.2106 0.03480 0.02728 0.0228 0.0401 1.0000
13.000 1.2028 0.03781 0.03039 0.0238 0.0383 1.0000
13.250 1.1943 0.04120 0.03390 0.0241 0.0370 1.0000
13.500 1.1893 0.04448 0.03733 0.0240 0.0359 1.0000
13.750 1.1829 0.04810 0.04108 0.0236 0.0349 1.0000
14.000 1.1748 0.05206 0.04516 0.0228 0.0340 1.0000
14.250 1.1657 0.05625 0.04947 0.0218 0.0332 1.0000
14.500 1.1559 0.06058 0.05390 0.0207 0.0326 1.0000
14.750 1.1454 0.06503 0.05842 0.0196 0.0320 1.0000
15.000 1.1349 0.06943 0.06286 0.0186 0.0314 1.0000
15.250 1.1286 0.07316 0.06661 0.0181 0.0307 1.0000
15.500 1.1266 0.07666 0.07021 0.0173 0.0303 1.0000
15.750 1.1253 0.08000 0.07365 0.0166 0.0298 1.0000
16.000 1.1251 0.08322 0.07694 0.0161 0.0293 1.0000
16.250 1.1255 0.08637 0.08018 0.0155 0.0288 1.0000
16.500 1.1271 0.08933 0.08321 0.0151 0.0283 1.0000
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