Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 4 (fg4-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.33 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg4-il-1000000-n5.txt Download as CSV file: xf-fg4-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1799 0.10659 0.10468 -0.0660 0.9791 0.0163
-11.250 -0.1733 0.10289 0.10098 -0.0682 0.9771 0.0169
-10.750 -0.1975 0.09994 0.09810 -0.0597 0.9387 0.0163
-10.500 -0.1850 0.09590 0.09405 -0.0634 0.9331 0.0164
-10.250 -0.1699 0.09171 0.08985 -0.0679 0.9285 0.0166
-10.000 -0.1627 0.08496 0.08307 -0.0749 0.9250 0.0176
-9.750 -0.1442 0.08103 0.07912 -0.0800 0.9220 0.0177
-9.500 -0.1175 0.07866 0.07673 -0.0844 0.9187 0.0180
-9.250 -0.1000 0.07195 0.06996 -0.0941 0.9147 0.0178
-9.000 -0.0666 0.07000 0.06798 -0.0995 0.9109 0.0184
-8.750 -0.0483 0.06094 0.05881 -0.1159 0.9032 0.0179
-8.500 -0.0215 0.05874 0.05656 -0.1212 0.8959 0.0185
-8.000 -0.0162 0.04958 0.04719 -0.1283 0.8758 0.0182
-7.750 -0.0099 0.04581 0.04330 -0.1297 0.8684 0.0182
-7.500 -0.0087 0.04258 0.03997 -0.1286 0.8614 0.0183
-7.250 -0.0010 0.04009 0.03739 -0.1275 0.8537 0.0184
-7.000 0.0050 0.03746 0.03463 -0.1256 0.8458 0.0186
-6.750 0.0087 0.03474 0.03176 -0.1228 0.8349 0.0187
-6.500 0.0120 0.03226 0.02912 -0.1194 0.8198 0.0188
-6.250 0.0119 0.02984 0.02645 -0.1147 0.7900 0.0188
-6.000 0.0104 0.02807 0.02434 -0.1092 0.7449 0.0190
-5.750 0.0129 0.02611 0.02208 -0.1044 0.7142 0.0193
-5.500 0.0160 0.02391 0.01956 -0.0996 0.6904 0.0196
-5.250 0.0194 0.02162 0.01696 -0.0946 0.6701 0.0198
-5.000 0.0259 0.01985 0.01490 -0.0902 0.6490 0.0198
-4.750 0.0277 0.01721 0.01182 -0.0845 0.6266 0.0201
-4.500 0.0347 0.01538 0.00958 -0.0799 0.6032 0.0203
-4.250 0.0493 0.01424 0.00816 -0.0769 0.5914 0.0206
-4.000 0.0651 0.01349 0.00721 -0.0742 0.5750 0.0207
-3.750 0.0836 0.01311 0.00671 -0.0721 0.5608 0.0209
-3.500 0.1025 0.01300 0.00651 -0.0700 0.5423 0.0211
-3.250 0.1226 0.01263 0.00603 -0.0682 0.5291 0.0212
-3.000 0.1425 0.01240 0.00569 -0.0663 0.5129 0.0213
-2.750 0.1632 0.01218 0.00538 -0.0646 0.5022 0.0214
-2.500 0.1851 0.01196 0.00511 -0.0631 0.4923 0.0217
-2.250 0.2062 0.01173 0.00480 -0.0615 0.4808 0.0218
-2.000 0.2267 0.01157 0.00453 -0.0598 0.4640 0.0220
-1.750 0.2464 0.01148 0.00431 -0.0579 0.4394 0.0222
-1.500 0.2658 0.01139 0.00409 -0.0560 0.4143 0.0223
-1.000 0.3016 0.01146 0.00383 -0.0516 0.3466 0.0228
-0.750 0.3188 0.01151 0.00371 -0.0492 0.3136 0.0230
-0.500 0.3357 0.01170 0.00372 -0.0469 0.2761 0.0232
-0.250 0.3552 0.01175 0.00368 -0.0450 0.2577 0.0236
0.000 0.3699 0.01195 0.00365 -0.0422 0.2150 0.0237
0.250 0.3676 0.01304 0.00413 -0.0363 0.0632 0.0238
0.500 0.3870 0.01311 0.00416 -0.0344 0.0554 0.0240
0.750 0.4070 0.01312 0.00415 -0.0327 0.0536 0.0241
1.000 0.4264 0.01306 0.00408 -0.0308 0.0513 0.0244
1.250 0.4470 0.01306 0.00408 -0.0292 0.0503 0.0251
1.500 0.4680 0.01310 0.00411 -0.0277 0.0497 0.0252
1.750 0.4891 0.01316 0.00418 -0.0263 0.0489 0.0258
2.000 0.5104 0.01322 0.00424 -0.0249 0.0485 0.0263
2.250 0.5316 0.01331 0.00432 -0.0236 0.0476 0.0266
2.500 0.5528 0.01340 0.00440 -0.0222 0.0472 0.0272
2.750 0.5734 0.01352 0.00453 -0.0208 0.0465 0.0275
3.000 0.5940 0.01367 0.00467 -0.0193 0.0459 0.0280
3.250 0.6146 0.01382 0.00483 -0.0180 0.0452 0.0290
3.500 0.6362 0.01394 0.00496 -0.0168 0.0450 0.0300
3.750 0.6577 0.01409 0.00511 -0.0156 0.0447 0.0314
4.000 0.6790 0.01425 0.00528 -0.0145 0.0445 0.0323
4.250 0.7000 0.01443 0.00547 -0.0133 0.0443 0.0334
4.500 0.7214 0.01461 0.00565 -0.0122 0.0437 0.0355
5.000 1.0654 0.01473 0.00773 -0.0787 0.0415 1.0000
5.250 1.0826 0.01501 0.00800 -0.0768 0.0412 1.0000
5.500 1.0994 0.01530 0.00829 -0.0747 0.0410 1.0000
5.750 1.1153 0.01564 0.00864 -0.0726 0.0408 1.0000
6.000 1.1302 0.01605 0.00906 -0.0703 0.0405 1.0000
6.250 1.1459 0.01642 0.00944 -0.0682 0.0404 1.0000
6.500 1.1620 0.01676 0.00979 -0.0662 0.0403 1.0000
6.750 1.1780 0.01711 0.01015 -0.0642 0.0402 1.0000
7.000 1.1937 0.01748 0.01054 -0.0623 0.0401 1.0000
7.250 1.2095 0.01785 0.01092 -0.0603 0.0400 1.0000
7.500 1.2264 0.01817 0.01125 -0.0586 0.0397 1.0000
7.750 1.2423 0.01855 0.01164 -0.0568 0.0395 1.0000
8.000 1.2571 0.01897 0.01208 -0.0549 0.0394 1.0000
8.250 1.2732 0.01935 0.01247 -0.0532 0.0390 1.0000
8.500 1.2898 0.01971 0.01283 -0.0516 0.0385 1.0000
8.750 1.3044 0.02017 0.01331 -0.0498 0.0383 1.0000
9.000 1.3179 0.02071 0.01388 -0.0479 0.0380 1.0000
9.250 1.3310 0.02128 0.01447 -0.0460 0.0379 1.0000
9.500 1.3454 0.02179 0.01500 -0.0443 0.0376 1.0000
9.750 1.3608 0.02227 0.01548 -0.0429 0.0372 1.0000
10.000 1.3729 0.02294 0.01619 -0.0410 0.0371 1.0000
10.250 1.3868 0.02354 0.01678 -0.0395 0.0366 1.0000
10.500 1.3990 0.02424 0.01751 -0.0378 0.0362 1.0000
10.750 1.4103 0.02502 0.01832 -0.0361 0.0359 1.0000
11.000 1.4253 0.02559 0.01891 -0.0349 0.0355 1.0000
11.250 1.4363 0.02643 0.01979 -0.0333 0.0354 1.0000
11.500 1.4488 0.02720 0.02059 -0.0320 0.0347 1.0000
11.750 1.4636 0.02783 0.02124 -0.0309 0.0338 1.0000
12.000 1.4752 0.02868 0.02211 -0.0296 0.0332 1.0000
12.250 1.4881 0.02948 0.02290 -0.0285 0.0322 1.0000
12.500 1.4976 0.03055 0.02402 -0.0272 0.0315 1.0000
12.750 1.4969 0.03244 0.02578 -0.0252 0.0155 1.0000
13.000 1.4951 0.03455 0.02798 -0.0233 0.0134 1.0000
13.250 1.4967 0.03650 0.03001 -0.0220 0.0125 1.0000
13.500 1.4997 0.03842 0.03200 -0.0209 0.0120 1.0000
13.750 1.5003 0.04065 0.03431 -0.0199 0.0115 1.0000
14.000 1.4990 0.04315 0.03690 -0.0190 0.0108 1.0000
14.250 1.5007 0.04544 0.03927 -0.0184 0.0107 1.0000
14.500 1.5003 0.04803 0.04194 -0.0179 0.0103 1.0000
14.750 1.5004 0.05064 0.04464 -0.0176 0.0102 1.0000
15.000 1.4984 0.05355 0.04762 -0.0174 0.0099 1.0000
15.250 1.4948 0.05669 0.05086 -0.0173 0.0098 1.0000
15.500 1.4906 0.06000 0.05425 -0.0173 0.0095 1.0000
15.750 1.4846 0.06358 0.05792 -0.0175 0.0093 1.0000
16.000 1.4784 0.06724 0.06168 -0.0178 0.0092 1.0000
16.250 1.4706 0.07116 0.06570 -0.0182 0.0090 1.0000
16.500 1.4642 0.07500 0.06962 -0.0187 0.0090 1.0000
16.750 1.4579 0.07888 0.07360 -0.0193 0.0089 1.0000
17.000 1.4491 0.08315 0.07796 -0.0201 0.0088 1.0000
17.250 1.4422 0.08721 0.08211 -0.0209 0.0087 1.0000
17.500 1.4343 0.09148 0.08647 -0.0219 0.0086 1.0000
17.750 1.4260 0.09586 0.09094 -0.0229 0.0083 1.0000
18.000 1.4174 0.10032 0.09549 -0.0241 0.0083 1.0000
18.250 1.4083 0.10488 0.10014 -0.0253 0.0083 1.0000
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Polar data table (+)
Polar graphs
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