Fage & Collins 1 (fg1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Fage & Collins 1 (fg1-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.87 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg1-il-1000000.txt Download as CSV file: xf-fg1-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 1
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4340 0.09096 0.08932 -0.0236 1.0000 0.0164
-9.000 -0.4348 0.08860 0.08699 -0.0232 1.0000 0.0165
-8.750 -0.4387 0.08628 0.08469 -0.0227 0.9999 0.0167
-8.500 -0.4243 0.08256 0.08098 -0.0277 0.9980 0.0169
-8.250 -0.4091 0.07824 0.07664 -0.0345 0.9950 0.0172
-8.000 -0.3881 0.07323 0.07162 -0.0420 0.9914 0.0178
-7.750 -0.3552 0.06392 0.06218 -0.0582 0.9864 0.0195
-7.500 -0.3309 0.05776 0.05590 -0.0651 0.9834 0.0196
-7.250 -0.3122 0.05283 0.05084 -0.0684 0.9774 0.0196
-7.000 -0.2625 0.03139 0.02943 -0.0727 0.9659 0.0200
-6.750 -0.2815 0.04306 0.04084 -0.0729 0.9670 0.0200
-6.500 -0.2586 0.04072 0.03844 -0.0744 0.9635 0.0203
-6.250 -0.2387 0.03853 0.03617 -0.0748 0.9576 0.0206
-6.000 -0.2171 0.03610 0.03363 -0.0753 0.9519 0.0210
-5.750 -0.1908 0.03329 0.03068 -0.0766 0.9487 0.0216
-5.500 -0.1612 0.03020 0.02721 -0.0763 0.9427 0.0237
-5.250 -0.1313 0.02761 0.02434 -0.0774 0.9391 0.0238
-4.750 -0.0731 0.02059 0.01679 -0.0806 0.9309 0.0245
-4.500 -0.0354 0.01913 0.01525 -0.0836 0.9268 0.0249
-4.250 0.0041 0.01784 0.01381 -0.0867 0.9219 0.0255
-4.000 0.0345 0.01676 0.01257 -0.0875 0.9142 0.0263
-3.750 0.0685 0.01587 0.01147 -0.0886 0.9081 0.0279
-3.500 0.0955 0.01618 0.01154 -0.0877 0.9004 0.0288
-3.250 0.1227 0.01550 0.01068 -0.0875 0.8944 0.0289
-3.000 0.1427 0.01294 0.00793 -0.0861 0.8873 0.0298
-2.750 0.1677 0.01217 0.00716 -0.0856 0.8805 0.0305
-2.500 0.1929 0.01162 0.00655 -0.0850 0.8736 0.0311
-2.250 0.2168 0.01114 0.00601 -0.0840 0.8665 0.0323
-2.000 0.2431 0.01099 0.00577 -0.0834 0.8599 0.0341
-1.750 0.2660 0.01012 0.00481 -0.0821 0.8527 0.0367
-1.500 0.2916 0.00963 0.00435 -0.0816 0.8450 0.0381
-1.250 0.3152 0.00937 0.00408 -0.0805 0.8355 0.0405
-1.000 0.3390 0.00888 0.00356 -0.0796 0.8260 0.0458
-0.750 0.3626 0.00861 0.00330 -0.0785 0.8139 0.0487
-0.500 0.3862 0.00861 0.00325 -0.0774 0.7981 0.0517
-0.250 0.4080 0.00808 0.00254 -0.0752 0.7743 0.0357
0.000 0.4279 0.00816 0.00248 -0.0732 0.7386 0.0350
0.250 0.4432 0.00773 0.00191 -0.0703 0.7005 0.0324
0.500 0.4602 0.00775 0.00175 -0.0677 0.6554 0.0318
0.750 0.4770 0.00787 0.00166 -0.0651 0.6052 0.0317
1.000 0.4952 0.00800 0.00161 -0.0630 0.5612 0.0323
1.250 0.5153 0.00811 0.00158 -0.0612 0.5281 0.0328
1.500 0.5369 0.00819 0.00157 -0.0598 0.5023 0.0336
1.750 0.5589 0.00828 0.00157 -0.0585 0.4792 0.0341
2.000 0.5815 0.00836 0.00158 -0.0573 0.4576 0.0346
2.250 0.6041 0.00845 0.00159 -0.0562 0.4357 0.0357
2.500 0.6265 0.00856 0.00162 -0.0550 0.4143 0.0370
2.750 0.6489 0.00869 0.00166 -0.0538 0.3898 0.0394
3.000 0.8138 0.00776 0.00249 -0.0868 0.3018 1.0000
3.250 0.8340 0.00806 0.00263 -0.0853 0.2681 1.0000
3.500 0.8540 0.00838 0.00278 -0.0837 0.2347 1.0000
3.750 0.8746 0.00867 0.00294 -0.0823 0.2101 1.0000
4.000 0.8959 0.00892 0.00311 -0.0809 0.1938 1.0000
4.250 0.9177 0.00914 0.00328 -0.0797 0.1834 1.0000
4.500 0.9396 0.00934 0.00345 -0.0785 0.1762 1.0000
4.750 0.9620 0.00953 0.00363 -0.0774 0.1696 1.0000
5.000 0.9838 0.00974 0.00380 -0.0763 0.1620 1.0000
5.250 1.0060 0.00993 0.00399 -0.0752 0.1556 1.0000
5.500 1.0283 0.01011 0.00417 -0.0741 0.1495 1.0000
5.750 1.0499 0.01034 0.00437 -0.0729 0.1422 1.0000
6.000 1.0724 0.01051 0.00454 -0.0719 0.1353 1.0000
6.250 1.0940 0.01074 0.00476 -0.0707 0.1266 1.0000
6.500 1.1150 0.01101 0.00497 -0.0695 0.1141 1.0000
6.750 1.1344 0.01139 0.00524 -0.0679 0.0943 1.0000
7.000 1.1525 0.01186 0.00559 -0.0662 0.0777 1.0000
7.250 1.1715 0.01226 0.00595 -0.0646 0.0673 1.0000
7.500 1.1908 0.01263 0.00630 -0.0630 0.0589 1.0000
7.750 1.2096 0.01302 0.00667 -0.0614 0.0506 1.0000
8.000 1.2276 0.01347 0.00707 -0.0597 0.0414 1.0000
8.250 1.2431 0.01410 0.00760 -0.0575 0.0289 1.0000
8.500 1.2597 0.01464 0.00811 -0.0555 0.0227 1.0000
8.750 1.2762 0.01518 0.00865 -0.0536 0.0196 1.0000
9.000 1.2932 0.01567 0.00917 -0.0517 0.0181 1.0000
9.250 1.3101 0.01614 0.00969 -0.0498 0.0168 1.0000
9.500 1.3256 0.01670 0.01028 -0.0477 0.0158 1.0000
9.750 1.3358 0.01745 0.01111 -0.0446 0.0147 1.0000
10.000 1.3503 0.01783 0.01153 -0.0422 0.0143 1.0000
10.250 1.3635 0.01829 0.01205 -0.0397 0.0137 1.0000
10.500 1.3757 0.01882 0.01264 -0.0371 0.0132 1.0000
10.750 1.3871 0.01943 0.01330 -0.0344 0.0127 1.0000
11.000 1.3970 0.02013 0.01406 -0.0316 0.0123 1.0000
11.250 1.4030 0.02109 0.01510 -0.0282 0.0117 1.0000
11.500 1.4074 0.02215 0.01626 -0.0248 0.0114 1.0000
11.750 1.4175 0.02289 0.01709 -0.0223 0.0112 1.0000
12.000 1.4285 0.02360 0.01788 -0.0201 0.0110 1.0000
12.250 1.4360 0.02455 0.01891 -0.0175 0.0108 1.0000
12.500 1.4442 0.02549 0.01993 -0.0152 0.0105 1.0000
12.750 1.4511 0.02654 0.02106 -0.0129 0.0102 1.0000
13.000 1.4571 0.02770 0.02231 -0.0107 0.0100 1.0000
13.250 1.4619 0.02898 0.02367 -0.0086 0.0097 1.0000
13.500 1.4652 0.03044 0.02520 -0.0065 0.0095 1.0000
13.750 1.4673 0.03205 0.02690 -0.0046 0.0093 1.0000
14.000 1.4638 0.03422 0.02917 -0.0025 0.0091 1.0000
14.250 1.4557 0.03694 0.03201 -0.0005 0.0090 1.0000
14.500 1.4399 0.04066 0.03589 0.0011 0.0088 1.0000
14.750 1.4321 0.04389 0.03925 0.0018 0.0087 1.0000
15.000 1.4316 0.04656 0.04203 0.0019 0.0086 1.0000
15.250 1.4293 0.04964 0.04522 0.0017 0.0086 1.0000
15.500 1.4219 0.05356 0.04927 0.0010 0.0085 1.0000
15.750 1.4158 0.05760 0.05344 -0.0001 0.0084 1.0000
16.000 1.4050 0.06254 0.05851 -0.0018 0.0083 1.0000
16.250 1.3900 0.06826 0.06436 -0.0039 0.0084 1.0000
16.500 1.3845 0.07280 0.06902 -0.0059 0.0082 1.0000
16.750 1.3677 0.07913 0.07547 -0.0085 0.0082 1.0000
17.000 1.3557 0.08490 0.08136 -0.0111 0.0080 1.0000
17.250 1.3346 0.09208 0.08867 -0.0141 0.0081 1.0000
17.500 1.3205 0.09835 0.09505 -0.0169 0.0081 1.0000
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Polar data table (+)
Polar graphs
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