Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 4 (fg4-il) Reynolds number: 500,000 Max Cl/Cd: 58.75 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg4-il-500000-n5.txt Download as CSV file: xf-fg4-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1843 0.09300 0.09048 -0.0667 0.9691 0.0240
-9.750 -0.1939 0.09042 0.08794 -0.0649 0.9495 0.0240
-9.500 -0.1907 0.08657 0.08409 -0.0675 0.9394 0.0241
-9.250 -0.1815 0.08281 0.08033 -0.0707 0.9333 0.0241
-9.000 -0.1723 0.07799 0.07549 -0.0763 0.9279 0.0241
-8.750 -0.1615 0.07341 0.07090 -0.0822 0.9230 0.0241
-8.500 -0.1448 0.07061 0.06810 -0.0839 0.9199 0.0243
-8.250 -0.1308 0.06582 0.06325 -0.0906 0.9153 0.0243
-8.000 -0.1082 0.06252 0.05991 -0.0948 0.9112 0.0246
-7.750 -0.0821 0.05844 0.05576 -0.1009 0.9067 0.0248
-7.500 -0.0529 0.05424 0.05145 -0.1077 0.9024 0.0251
-7.250 -0.0285 0.05048 0.04759 -0.1126 0.8964 0.0255
-7.000 -0.0044 0.04671 0.04368 -0.1169 0.8891 0.0259
-6.750 0.0113 0.04075 0.03731 -0.1195 0.8808 0.0279
-6.500 0.0241 0.03770 0.03405 -0.1188 0.8722 0.0280
-6.000 0.0297 0.02966 0.02546 -0.1126 0.8542 0.0242
-5.750 0.0391 0.02781 0.02343 -0.1093 0.8442 0.0241
-5.500 0.0488 0.02600 0.02141 -0.1061 0.8317 0.0242
-5.250 0.0565 0.02451 0.01973 -0.1021 0.8146 0.0241
-5.000 0.0667 0.02315 0.01813 -0.0985 0.7895 0.0241
-4.750 0.0772 0.02167 0.01636 -0.0951 0.7581 0.0243
-4.500 0.0904 0.02105 0.01550 -0.0922 0.7236 0.0245
-4.250 0.1047 0.02081 0.01508 -0.0895 0.6945 0.0248
-4.000 0.1164 0.01993 0.01395 -0.0860 0.6702 0.0248
-3.750 0.1259 0.01834 0.01197 -0.0817 0.6502 0.0246
-3.500 0.1405 0.01759 0.01102 -0.0788 0.6341 0.0247
-3.250 0.1537 0.01671 0.00987 -0.0754 0.6126 0.0247
-3.000 0.1694 0.01613 0.00911 -0.0726 0.5953 0.0248
-2.500 0.2036 0.01522 0.00789 -0.0676 0.5629 0.0251
-2.250 0.2217 0.01478 0.00730 -0.0653 0.5476 0.0253
-2.000 0.2411 0.01439 0.00678 -0.0633 0.5356 0.0255
-1.750 0.2599 0.01409 0.00634 -0.0612 0.5215 0.0258
-1.500 0.2819 0.01371 0.00588 -0.0598 0.5121 0.0260
-1.250 0.3018 0.01346 0.00551 -0.0579 0.4985 0.0263
-1.000 0.3216 0.01324 0.00519 -0.0560 0.4845 0.0266
-0.750 0.3414 0.01305 0.00490 -0.0541 0.4672 0.0269
-0.500 0.3597 0.01304 0.00476 -0.0519 0.4452 0.0275
-0.250 0.3793 0.01294 0.00455 -0.0500 0.4276 0.0278
0.000 0.3955 0.01296 0.00441 -0.0475 0.3949 0.0279
0.250 0.4096 0.01313 0.00434 -0.0446 0.3524 0.0280
0.750 0.4423 0.01321 0.00418 -0.0398 0.2992 0.0286
1.000 0.4577 0.01337 0.00420 -0.0372 0.2675 0.0289
1.250 0.4738 0.01356 0.00425 -0.0349 0.2376 0.0296
1.500 0.4890 0.01382 0.00434 -0.0324 0.2036 0.0298
2.000 0.5027 0.01522 0.00505 -0.0244 0.0592 0.0308
2.250 0.5223 0.01533 0.00516 -0.0227 0.0560 0.0313
2.500 0.5425 0.01542 0.00525 -0.0212 0.0549 0.0320
2.750 0.5625 0.01555 0.00538 -0.0197 0.0537 0.0327
3.000 0.5829 0.01566 0.00551 -0.0183 0.0529 0.0344
3.250 0.6029 0.01584 0.00569 -0.0168 0.0519 0.0354
3.500 0.6226 0.01604 0.00589 -0.0153 0.0510 0.0367
3.750 0.6426 0.01623 0.00608 -0.0139 0.0505 0.0384
4.000 0.6629 0.01642 0.00629 -0.0126 0.0501 0.0409
4.250 0.6832 0.01662 0.00651 -0.0113 0.0498 0.0455
4.500 0.9793 0.01667 0.00859 -0.0724 0.0472 1.0000
4.750 0.9953 0.01702 0.00893 -0.0703 0.0470 1.0000
5.000 1.0112 0.01737 0.00928 -0.0681 0.0467 1.0000
5.250 1.0264 0.01778 0.00968 -0.0659 0.0463 1.0000
5.500 1.0411 0.01821 0.01012 -0.0636 0.0459 1.0000
5.750 1.0542 0.01872 0.01063 -0.0611 0.0456 1.0000
6.000 1.0663 0.01929 0.01122 -0.0585 0.0453 1.0000
6.250 1.0805 0.01975 0.01169 -0.0563 0.0452 1.0000
6.500 1.0948 0.02022 0.01218 -0.0542 0.0450 1.0000
6.750 1.1085 0.02073 0.01271 -0.0520 0.0449 1.0000
7.000 1.1214 0.02129 0.01329 -0.0498 0.0448 1.0000
7.250 1.1347 0.02185 0.01387 -0.0477 0.0446 1.0000
7.500 1.1470 0.02247 0.01452 -0.0455 0.0445 1.0000
7.750 1.1578 0.02319 0.01527 -0.0432 0.0445 1.0000
8.000 1.1685 0.02394 0.01606 -0.0410 0.0444 1.0000
8.250 1.1795 0.02470 0.01686 -0.0389 0.0443 1.0000
8.500 1.1904 0.02551 0.01769 -0.0369 0.0441 1.0000
8.750 1.2008 0.02636 0.01859 -0.0349 0.0439 1.0000
9.000 1.2095 0.02735 0.01962 -0.0329 0.0438 1.0000
9.250 1.2210 0.02819 0.02050 -0.0313 0.0433 1.0000
9.500 1.2305 0.02919 0.02155 -0.0295 0.0430 1.0000
9.750 1.2411 0.03016 0.02255 -0.0280 0.0426 1.0000
10.000 1.2511 0.03119 0.02362 -0.0265 0.0422 1.0000
10.250 1.2591 0.03241 0.02489 -0.0249 0.0419 1.0000
10.500 1.2679 0.03361 0.02613 -0.0236 0.0416 1.0000
10.750 1.2750 0.03501 0.02757 -0.0222 0.0413 1.0000
11.000 1.2826 0.03642 0.02902 -0.0211 0.0410 1.0000
11.250 1.2880 0.03807 0.03072 -0.0199 0.0409 1.0000
11.500 1.2890 0.04020 0.03292 -0.0187 0.0406 1.0000
11.750 1.2926 0.04218 0.03495 -0.0178 0.0403 1.0000
12.000 1.3009 0.04377 0.03661 -0.0172 0.0401 1.0000
12.250 1.3066 0.04566 0.03857 -0.0166 0.0399 1.0000
12.500 1.3175 0.04708 0.04006 -0.0163 0.0394 1.0000
12.750 1.3251 0.04886 0.04192 -0.0160 0.0390 1.0000
13.000 1.3307 0.05090 0.04403 -0.0157 0.0387 1.0000
13.250 1.3357 0.05305 0.04625 -0.0155 0.0383 1.0000
13.500 1.3431 0.05497 0.04824 -0.0155 0.0377 1.0000
13.750 1.3484 0.05714 0.05047 -0.0154 0.0373 1.0000
14.000 1.3567 0.05900 0.05239 -0.0155 0.0368 1.0000
14.250 1.3663 0.06075 0.05416 -0.0157 0.0360 1.0000
14.500 1.3694 0.06327 0.05676 -0.0158 0.0356 1.0000
14.750 1.3700 0.06610 0.05969 -0.0160 0.0352 1.0000
15.000 1.3719 0.06880 0.06248 -0.0162 0.0346 1.0000
15.250 1.3722 0.07175 0.06552 -0.0165 0.0340 1.0000
15.500 1.3768 0.07418 0.06803 -0.0169 0.0330 1.0000
15.750 1.3829 0.07642 0.07031 -0.0172 0.0318 1.0000
16.000 1.3777 0.08018 0.07418 -0.0178 0.0306 1.0000
16.250 1.3853 0.08228 0.07607 -0.0184 0.0151 1.0000
16.500 1.3713 0.08738 0.08129 -0.0194 0.0143 1.0000
16.750 1.3594 0.09227 0.08629 -0.0205 0.0138 1.0000
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Polar data table (+)
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