Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Fage & Collins 4 (fg4-il) Reynolds number: 1,000,000 Max Cl/Cd: 71.69 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg4-il-1000000.txt Download as CSV file: xf-fg4-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 4
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1050 0.09610 0.09441 -0.0649 0.9825 0.0201
-10.750 -0.0974 0.09269 0.09101 -0.0665 0.9802 0.0203
-10.500 -0.0882 0.08917 0.08750 -0.0685 0.9785 0.0206
-10.250 -0.0786 0.08558 0.08391 -0.0708 0.9771 0.0210
-10.000 -0.0694 0.08164 0.07996 -0.0734 0.9759 0.0214
-9.750 -0.0696 0.07858 0.07691 -0.0732 0.9687 0.0218
-9.500 -0.0796 0.07417 0.07251 -0.0746 0.9564 0.0226
-9.250 -0.1373 0.08331 0.08157 -0.0737 0.9764 0.0216
-9.000 -0.1417 0.07783 0.07609 -0.0792 0.9672 0.0226
-8.750 -0.1534 0.07427 0.07254 -0.0801 0.9472 0.0227
-8.500 -0.1531 0.06980 0.06806 -0.0850 0.9375 0.0227
-8.250 -0.1446 0.06428 0.06247 -0.0909 0.9314 0.0228
-8.000 -0.1244 0.05816 0.05625 -0.0978 0.9268 0.0228
-7.750 -0.1083 0.05218 0.05016 -0.1032 0.9224 0.0229
-7.500 -0.0800 0.04865 0.04655 -0.1080 0.9188 0.0231
-7.250 -0.0490 0.04558 0.04340 -0.1126 0.9148 0.0233
-7.000 -0.0185 0.04275 0.04047 -0.1167 0.9095 0.0235
-6.750 0.0158 0.03972 0.03731 -0.1215 0.9043 0.0238
-6.500 0.0427 0.03694 0.03439 -0.1241 0.8974 0.0241
-6.250 0.0634 0.03446 0.03177 -0.1247 0.8898 0.0246
-6.000 0.0801 0.02990 0.02666 -0.1228 0.8817 0.0265
-5.750 0.0798 0.02635 0.02287 -0.1188 0.8719 0.0268
-5.500 0.0906 0.02506 0.02151 -0.1159 0.8616 0.0269
-5.250 0.1047 0.02395 0.02030 -0.1136 0.8498 0.0271
-5.000 0.1120 0.02312 0.01939 -0.1094 0.8342 0.0272
-4.750 0.1172 0.02229 0.01845 -0.1048 0.8121 0.0274
-4.500 0.1221 0.02158 0.01755 -0.0999 0.7734 0.0276
-4.250 0.1265 0.02097 0.01664 -0.0949 0.7291 0.0278
-4.000 0.1371 0.02022 0.01569 -0.0912 0.7030 0.0282
-3.750 0.1473 0.01949 0.01474 -0.0874 0.6764 0.0286
-3.500 0.1601 0.01854 0.01356 -0.0838 0.6594 0.0298
-3.250 0.1736 0.01861 0.01320 -0.0794 0.6402 0.0308
-2.750 0.1951 0.01574 0.01005 -0.0725 0.6032 0.0317
-2.500 0.2119 0.01523 0.00945 -0.0700 0.5884 0.0320
-2.250 0.2302 0.01472 0.00883 -0.0678 0.5758 0.0324
-2.000 0.2482 0.01430 0.00829 -0.0656 0.5625 0.0333
-1.750 0.2639 0.01388 0.00752 -0.0622 0.5491 0.0362
-1.500 0.2849 0.01327 0.00691 -0.0608 0.5368 0.0368
-1.250 0.3058 0.01289 0.00648 -0.0592 0.5267 0.0374
-1.000 0.3257 0.01267 0.00618 -0.0573 0.5138 0.0387
-0.750 0.3447 0.01336 0.00670 -0.0549 0.5012 0.0410
-0.500 0.3739 0.01141 0.00450 -0.0544 0.4909 0.0310
-0.250 0.3948 0.01129 0.00430 -0.0528 0.4728 0.0309
0.000 0.4158 0.01105 0.00399 -0.0512 0.4536 0.0310
0.250 0.4357 0.01074 0.00359 -0.0493 0.4330 0.0312
0.500 0.4497 0.01076 0.00342 -0.0464 0.3887 0.0316
0.750 0.4662 0.01085 0.00336 -0.0439 0.3573 0.0316
1.000 0.4795 0.01107 0.00336 -0.0409 0.3106 0.0318
1.250 0.4951 0.01125 0.00339 -0.0383 0.2769 0.0323
1.500 0.5080 0.01161 0.00350 -0.0353 0.2279 0.0328
1.750 0.5179 0.01212 0.00369 -0.0317 0.1674 0.0329
2.000 0.5174 0.01314 0.00424 -0.0262 0.0614 0.0336
2.250 0.5378 0.01321 0.00429 -0.0247 0.0571 0.0343
2.500 0.5588 0.01328 0.00436 -0.0232 0.0559 0.0343
2.750 0.5800 0.01335 0.00443 -0.0218 0.0555 0.0356
3.000 0.6010 0.01343 0.00452 -0.0205 0.0544 0.0369
3.250 0.6222 0.01354 0.00464 -0.0192 0.0539 0.0383
3.500 0.6432 0.01368 0.00479 -0.0179 0.0532 0.0405
3.750 0.6641 0.01385 0.00496 -0.0166 0.0526 0.0431
4.000 0.6849 0.01403 0.00516 -0.0153 0.0519 0.0488
4.250 1.0115 0.01411 0.00725 -0.0840 0.0489 1.0000
4.500 1.0288 0.01435 0.00749 -0.0819 0.0485 1.0000
4.750 1.0454 0.01465 0.00779 -0.0798 0.0481 1.0000
5.000 1.0623 0.01494 0.00809 -0.0777 0.0481 1.0000
5.250 1.0791 0.01523 0.00838 -0.0757 0.0479 1.0000
5.500 1.0944 0.01558 0.00875 -0.0733 0.0476 1.0000
5.750 1.1098 0.01594 0.00912 -0.0711 0.0473 1.0000
6.000 1.1255 0.01630 0.00949 -0.0690 0.0471 1.0000
6.250 1.1410 0.01667 0.00988 -0.0668 0.0471 1.0000
6.500 1.1549 0.01711 0.01033 -0.0644 0.0468 1.0000
6.750 1.1690 0.01755 0.01079 -0.0621 0.0467 1.0000
7.000 1.1825 0.01803 0.01129 -0.0597 0.0467 1.0000
7.250 1.1963 0.01848 0.01177 -0.0575 0.0466 1.0000
7.500 1.2089 0.01902 0.01233 -0.0551 0.0463 1.0000
7.750 1.2223 0.01952 0.01284 -0.0529 0.0457 1.0000
8.000 1.2340 0.02012 0.01346 -0.0506 0.0454 1.0000
8.250 1.2452 0.02075 0.01412 -0.0482 0.0452 1.0000
8.500 1.2550 0.02147 0.01487 -0.0457 0.0451 1.0000
8.750 1.2624 0.02236 0.01579 -0.0430 0.0446 1.0000
9.000 1.2723 0.02314 0.01660 -0.0408 0.0446 1.0000
9.250 1.2715 0.02458 0.01810 -0.0373 0.0440 1.0000
9.500 1.2802 0.02551 0.01907 -0.0351 0.0440 1.0000
9.750 1.2756 0.02736 0.02099 -0.0316 0.0436 1.0000
10.000 1.2869 0.02822 0.02189 -0.0301 0.0435 1.0000
10.250 1.2999 0.02900 0.02269 -0.0288 0.0433 1.0000
10.500 1.3068 0.03023 0.02398 -0.0269 0.0433 1.0000
10.750 1.3206 0.03100 0.02478 -0.0259 0.0431 1.0000
11.000 1.3332 0.03190 0.02572 -0.0249 0.0429 1.0000
11.250 1.3488 0.03258 0.02643 -0.0242 0.0425 1.0000
11.500 1.3564 0.03392 0.02783 -0.0228 0.0423 1.0000
11.750 1.3698 0.03484 0.02878 -0.0221 0.0418 1.0000
12.000 1.3758 0.03641 0.03040 -0.0209 0.0416 1.0000
12.250 1.3934 0.03704 0.03106 -0.0207 0.0409 1.0000
12.500 1.3946 0.03914 0.03323 -0.0195 0.0409 1.0000
12.750 1.4146 0.03960 0.03369 -0.0195 0.0399 1.0000
13.000 1.4293 0.04053 0.03464 -0.0192 0.0393 1.0000
13.250 1.4361 0.04224 0.03638 -0.0186 0.0388 1.0000
13.500 1.4367 0.04464 0.03883 -0.0179 0.0383 1.0000
13.750 1.4330 0.04756 0.04184 -0.0173 0.0380 1.0000
14.000 1.4466 0.04871 0.04303 -0.0172 0.0376 1.0000
14.250 1.4857 0.04710 0.04138 -0.0177 0.0366 1.0000
14.500 1.5112 0.04692 0.04119 -0.0177 0.0355 1.0000
14.750 1.5469 0.04561 0.03972 -0.0181 0.0330 1.0000
15.000 1.5554 0.04721 0.04138 -0.0178 0.0318 1.0000
15.250 1.5613 0.04908 0.04307 -0.0176 0.0177 1.0000
15.500 1.5399 0.05414 0.04824 -0.0171 0.0145 1.0000
15.750 1.5369 0.05721 0.05140 -0.0171 0.0143 1.0000
16.000 1.5223 0.06178 0.05610 -0.0172 0.0134 1.0000
16.250 1.5168 0.06530 0.05971 -0.0174 0.0133 1.0000
16.500 1.5044 0.06979 0.06432 -0.0178 0.0128 1.0000
16.750 1.4958 0.07389 0.06852 -0.0183 0.0126 1.0000
17.000 1.4839 0.07849 0.07324 -0.0191 0.0123 1.0000
17.250 1.4751 0.08273 0.07758 -0.0198 0.0122 1.0000
17.500 1.4661 0.08707 0.08202 -0.0207 0.0121 1.0000
17.750 1.4543 0.09190 0.08696 -0.0218 0.0119 1.0000
18.000 1.4429 0.09674 0.09190 -0.0230 0.0117 1.0000
18.250 1.4330 0.10138 0.09664 -0.0242 0.0117 1.0000
18.500 1.4230 0.10609 0.10144 -0.0255 0.0116 1.0000
18.750 1.4103 0.11131 0.10677 -0.0271 0.0114 1.0000
19.000 1.3992 0.11628 0.11184 -0.0287 0.0112 1.0000
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Polar data table (+)
Polar graphs
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