Fage & Collins 1 (fg1-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 1 (fg1-il) Reynolds number: 500,000 Max Cl/Cd: 82.16 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg1-il-500000-n5.txt Download as CSV file: xf-fg1-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4196 0.09509 0.09272 -0.0242 1.0000 0.0173
-9.250 -0.4264 0.09091 0.08858 -0.0252 1.0000 0.0167
-9.000 -0.4307 0.08796 0.08566 -0.0253 1.0000 0.0168
-8.750 -0.4254 0.08490 0.08262 -0.0274 0.9990 0.0170
-8.250 -0.3980 0.07415 0.07184 -0.0438 0.9896 0.0194
-8.000 -0.3800 0.06889 0.06654 -0.0505 0.9858 0.0193
-7.500 -0.3519 0.05659 0.05403 -0.0623 0.9693 0.0199
-7.250 -0.3325 0.05585 0.05330 -0.0626 0.9656 0.0204
-7.000 -0.3112 0.05140 0.04866 -0.0661 0.9556 0.0233
-6.750 -0.2925 0.04606 0.04307 -0.0683 0.9482 0.0235
-6.500 -0.2726 0.04195 0.03875 -0.0696 0.9432 0.0235
-6.250 -0.2501 0.03802 0.03459 -0.0709 0.9402 0.0235
-6.000 -0.2285 0.03456 0.03084 -0.0713 0.9357 0.0236
-5.500 -0.1791 0.03023 0.02640 -0.0739 0.9295 0.0245
-5.250 -0.1468 0.02836 0.02438 -0.0760 0.9267 0.0253
-5.000 -0.1160 0.02572 0.02149 -0.0774 0.9219 0.0255
-4.750 -0.0822 0.02325 0.01872 -0.0791 0.9177 0.0256
-4.500 -0.0481 0.02050 0.01558 -0.0806 0.9138 0.0249
-4.250 -0.0161 0.01888 0.01371 -0.0817 0.9087 0.0250
-4.000 0.0146 0.01782 0.01248 -0.0825 0.9027 0.0257
-3.750 0.0478 0.01604 0.01035 -0.0834 0.8970 0.0250
-3.500 0.0722 0.01506 0.00919 -0.0826 0.8888 0.0250
-3.250 0.1030 0.01420 0.00816 -0.0831 0.8819 0.0252
-3.000 0.1261 0.01352 0.00736 -0.0819 0.8744 0.0253
-2.750 0.1538 0.01290 0.00663 -0.0818 0.8680 0.0255
-2.500 0.1780 0.01236 0.00600 -0.0808 0.8595 0.0257
-2.250 0.2046 0.01187 0.00541 -0.0804 0.8502 0.0259
-2.000 0.2281 0.01152 0.00501 -0.0793 0.8393 0.0265
-1.750 0.2527 0.01111 0.00455 -0.0784 0.8296 0.0267
-1.500 0.2777 0.01072 0.00412 -0.0776 0.8195 0.0267
-1.250 0.3015 0.01036 0.00372 -0.0765 0.8063 0.0268
-1.000 0.3245 0.01006 0.00336 -0.0753 0.7862 0.0269
-0.750 0.3468 0.00983 0.00303 -0.0739 0.7590 0.0270
-0.500 0.3677 0.00971 0.00276 -0.0721 0.7248 0.0273
-0.250 0.3874 0.00967 0.00257 -0.0702 0.6864 0.0276
0.000 0.4049 0.00975 0.00243 -0.0678 0.6382 0.0279
0.250 0.4211 0.00990 0.00235 -0.0651 0.5849 0.0281
0.750 0.4583 0.01004 0.00219 -0.0611 0.5127 0.0288
1.000 0.4792 0.01002 0.00210 -0.0596 0.4904 0.0297
1.250 0.5012 0.01005 0.00208 -0.0583 0.4699 0.0306
1.500 0.5233 0.01011 0.00207 -0.0570 0.4502 0.0314
1.750 0.5454 0.01019 0.00207 -0.0558 0.4291 0.0318
2.000 0.5676 0.01028 0.00209 -0.0546 0.4073 0.0324
2.250 0.5897 0.01041 0.00213 -0.0534 0.3854 0.0330
2.500 0.6122 0.01053 0.00218 -0.0522 0.3662 0.0340
2.750 0.6347 0.01067 0.00225 -0.0511 0.3467 0.0348
3.000 0.6570 0.01082 0.00233 -0.0500 0.3273 0.0371
4.000 0.8665 0.01075 0.00375 -0.0745 0.1910 1.0000
4.250 0.8880 0.01100 0.00395 -0.0733 0.1814 1.0000
4.500 0.9095 0.01125 0.00416 -0.0720 0.1733 1.0000
4.750 0.9313 0.01147 0.00438 -0.0709 0.1677 1.0000
5.000 0.9532 0.01168 0.00460 -0.0697 0.1626 1.0000
5.250 0.9745 0.01194 0.00484 -0.0685 0.1569 1.0000
5.500 0.9963 0.01216 0.00508 -0.0673 0.1520 1.0000
5.750 1.0180 0.01239 0.00532 -0.0661 0.1458 1.0000
6.000 1.0389 0.01266 0.00558 -0.0649 0.1378 1.0000
6.250 1.0601 0.01292 0.00582 -0.0636 0.1280 1.0000
6.500 1.0809 0.01320 0.00609 -0.0624 0.1167 1.0000
6.750 1.0999 0.01362 0.00639 -0.0608 0.0969 1.0000
7.000 1.1183 0.01407 0.00676 -0.0592 0.0818 1.0000
7.250 1.1367 0.01452 0.00716 -0.0575 0.0712 1.0000
7.500 1.1551 0.01496 0.00759 -0.0559 0.0630 1.0000
7.750 1.1736 0.01538 0.00801 -0.0543 0.0556 1.0000
8.000 1.1914 0.01585 0.00846 -0.0526 0.0488 1.0000
8.250 1.2087 0.01633 0.00893 -0.0508 0.0418 1.0000
8.500 1.2256 0.01684 0.00944 -0.0490 0.0345 1.0000
8.750 1.2408 0.01746 0.01002 -0.0469 0.0265 1.0000
9.000 1.2546 0.01806 0.01061 -0.0445 0.0210 1.0000
9.250 1.2680 0.01862 0.01119 -0.0421 0.0182 1.0000
9.500 1.2802 0.01925 0.01185 -0.0394 0.0160 1.0000
9.750 1.2939 0.01978 0.01245 -0.0371 0.0154 1.0000
10.000 1.3071 0.02035 0.01310 -0.0347 0.0143 1.0000
10.250 1.3195 0.02099 0.01380 -0.0323 0.0135 1.0000
10.500 1.3306 0.02174 0.01461 -0.0298 0.0128 1.0000
10.750 1.3396 0.02263 0.01559 -0.0270 0.0120 1.0000
11.000 1.3525 0.02326 0.01630 -0.0249 0.0115 1.0000
11.250 1.3629 0.02406 0.01720 -0.0226 0.0111 1.0000
11.500 1.3727 0.02490 0.01813 -0.0203 0.0107 1.0000
11.750 1.3814 0.02585 0.01917 -0.0179 0.0102 1.0000
12.000 1.3896 0.02684 0.02026 -0.0157 0.0099 1.0000
12.250 1.3947 0.02808 0.02159 -0.0132 0.0095 1.0000
12.500 1.3986 0.02945 0.02305 -0.0108 0.0093 1.0000
12.750 1.3991 0.03112 0.02483 -0.0084 0.0090 1.0000
13.000 1.4008 0.03278 0.02660 -0.0063 0.0088 1.0000
13.250 1.4043 0.03436 0.02831 -0.0045 0.0087 1.0000
13.500 1.4060 0.03618 0.03026 -0.0029 0.0086 1.0000
13.750 1.4044 0.03839 0.03259 -0.0014 0.0085 1.0000
14.000 1.4034 0.04069 0.03503 -0.0003 0.0083 1.0000
14.250 1.4008 0.04332 0.03778 0.0005 0.0081 1.0000
14.500 1.3975 0.04620 0.04079 0.0009 0.0079 1.0000
14.750 1.3912 0.04965 0.04439 0.0008 0.0078 1.0000
15.000 1.3878 0.05299 0.04784 0.0003 0.0077 1.0000
15.250 1.3781 0.05743 0.05244 -0.0008 0.0076 1.0000
15.500 1.3698 0.06199 0.05713 -0.0023 0.0075 1.0000
15.750 1.3576 0.06736 0.06264 -0.0044 0.0074 1.0000
16.000 1.3422 0.07346 0.06889 -0.0069 0.0073 1.0000
16.250 1.3265 0.07974 0.07532 -0.0096 0.0073 1.0000
16.500 1.3133 0.08574 0.08144 -0.0123 0.0072 1.0000
16.750 1.2909 0.09336 0.08921 -0.0156 0.0073 1.0000
17.000 1.2744 0.10016 0.09614 -0.0186 0.0072 1.0000
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Polar data table (+)
Polar graphs
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