Fage & Collins 2 (fg2-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: Fage & Collins 2 (fg2-il) Reynolds number: 200,000 Max Cl/Cd: 69.8 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg2-il-200000.txt Download as CSV file: xf-fg2-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 2
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4205 0.10680 0.10325 -0.0226 1.0000 0.0276
-9.000 -0.4218 0.10378 0.10028 -0.0242 1.0000 0.0277
-8.750 -0.4256 0.10084 0.09739 -0.0257 1.0000 0.0277
-8.500 -0.3207 0.08359 0.08032 -0.0229 1.0000 0.0303
-8.250 -0.3219 0.08026 0.07703 -0.0230 1.0000 0.0308
-8.000 -0.4227 0.08886 0.08552 -0.0223 1.0000 0.0286
-7.750 -0.4232 0.08599 0.08268 -0.0211 1.0000 0.0290
-7.500 -0.4227 0.08292 0.07965 -0.0212 1.0000 0.0294
-7.250 -0.4217 0.07978 0.07653 -0.0213 1.0000 0.0301
-7.000 -0.4203 0.07661 0.07338 -0.0220 1.0000 0.0304
-6.750 -0.4182 0.07339 0.07015 -0.0225 1.0000 0.0312
-6.500 -0.4150 0.07009 0.06685 -0.0231 1.0000 0.0320
-6.250 -0.4102 0.06672 0.06344 -0.0238 1.0000 0.0335
-6.000 -0.3987 0.06350 0.06007 -0.0258 1.0000 0.0355
-5.750 -0.3865 0.06155 0.05775 -0.0262 1.0000 0.0364
-5.500 -0.3868 0.05571 0.05193 -0.0250 1.0000 0.0371
-5.250 -0.3822 0.05254 0.04882 -0.0232 1.0000 0.0380
-5.000 -0.3749 0.05002 0.04629 -0.0216 1.0000 0.0390
-4.750 -0.3655 0.04759 0.04379 -0.0201 1.0000 0.0405
-4.500 -0.3541 0.04509 0.04116 -0.0187 1.0000 0.0427
-4.250 -0.3320 0.04509 0.04052 -0.0166 1.0000 0.0475
-4.000 -0.3136 0.03879 0.03426 -0.0185 0.9970 0.0497
-3.500 -0.2353 0.03305 0.02807 -0.0256 0.9844 0.0646
-3.250 -0.1976 0.03073 0.02534 -0.0278 0.9756 0.0769
-3.000 -0.1608 0.02883 0.02315 -0.0300 0.9670 0.0908
-2.750 -0.1244 0.02634 0.02067 -0.0329 0.9608 0.1083
-1.750 0.0004 0.01983 0.01400 -0.0374 0.9238 0.2538
-1.500 0.0676 0.01757 0.01012 -0.0373 0.9194 0.0753
-1.250 0.1064 0.01562 0.00812 -0.0388 0.9094 0.0689
-1.000 0.1494 0.01443 0.00681 -0.0411 0.8978 0.0666
-0.750 0.1980 0.01343 0.00577 -0.0450 0.8843 0.0663
-0.500 0.2489 0.01254 0.00485 -0.0494 0.8658 0.0647
-0.250 0.2926 0.01192 0.00419 -0.0524 0.8373 0.0647
0.000 0.3299 0.01153 0.00368 -0.0541 0.8000 0.0663
0.250 0.3629 0.01136 0.00330 -0.0548 0.7598 0.0686
0.500 0.3906 0.01136 0.00307 -0.0544 0.7237 0.0738
0.750 0.4156 0.01138 0.00291 -0.0535 0.6936 0.0822
1.000 0.4297 0.01026 0.00293 -0.0509 0.6699 0.5223
1.250 0.5879 0.00987 0.00318 -0.0798 0.6242 1.0000
1.500 0.6097 0.01013 0.00323 -0.0784 0.6009 1.0000
1.750 0.6313 0.01036 0.00333 -0.0770 0.5779 1.0000
2.000 0.6529 0.01062 0.00341 -0.0756 0.5562 1.0000
2.250 0.6746 0.01084 0.00353 -0.0743 0.5350 1.0000
2.500 0.6965 0.01107 0.00364 -0.0730 0.5155 1.0000
2.750 0.7186 0.01131 0.00377 -0.0717 0.4982 1.0000
3.000 0.7410 0.01155 0.00394 -0.0706 0.4823 1.0000
3.250 0.7637 0.01178 0.00411 -0.0695 0.4679 1.0000
3.500 0.7864 0.01200 0.00429 -0.0684 0.4542 1.0000
3.750 0.8090 0.01222 0.00448 -0.0674 0.4408 1.0000
4.000 0.8320 0.01245 0.00472 -0.0664 0.4292 1.0000
4.250 0.8550 0.01270 0.00495 -0.0654 0.4187 1.0000
4.500 0.8779 0.01297 0.00518 -0.0644 0.4085 1.0000
4.750 0.9006 0.01320 0.00545 -0.0634 0.3978 1.0000
5.000 0.9235 0.01345 0.00576 -0.0625 0.3877 1.0000
5.250 0.9458 0.01373 0.00605 -0.0614 0.3770 1.0000
5.500 0.9666 0.01397 0.00630 -0.0600 0.3620 1.0000
5.750 0.9865 0.01420 0.00654 -0.0585 0.3437 1.0000
6.000 1.0072 0.01447 0.00687 -0.0571 0.3287 1.0000
6.250 1.0273 0.01474 0.00717 -0.0556 0.3116 1.0000
6.500 1.0463 0.01499 0.00744 -0.0540 0.2877 1.0000
6.750 1.0656 0.01527 0.00773 -0.0524 0.2611 1.0000
7.000 1.0840 0.01564 0.00804 -0.0507 0.2242 1.0000
7.250 1.0983 0.01640 0.00854 -0.0485 0.1771 1.0000
7.500 1.1109 0.01741 0.00931 -0.0460 0.1382 1.0000
7.750 1.1210 0.01871 0.01022 -0.0431 0.0675 1.0000
8.000 1.1270 0.02029 0.01154 -0.0395 0.0386 1.0000
8.250 1.1379 0.02144 0.01275 -0.0365 0.0331 1.0000
8.500 1.1503 0.02240 0.01386 -0.0339 0.0310 1.0000
8.750 1.1615 0.02337 0.01498 -0.0311 0.0283 1.0000
9.000 1.1692 0.02454 0.01626 -0.0279 0.0266 1.0000
9.250 1.1730 0.02585 0.01768 -0.0241 0.0257 1.0000
9.500 1.1716 0.02727 0.01918 -0.0195 0.0251 1.0000
9.750 1.1690 0.02897 0.02096 -0.0150 0.0245 1.0000
10.000 1.1714 0.03067 0.02273 -0.0115 0.0242 1.0000
10.250 1.1782 0.03225 0.02441 -0.0088 0.0240 1.0000
10.500 1.1869 0.03401 0.02628 -0.0064 0.0238 1.0000
10.750 1.1966 0.03579 0.02822 -0.0043 0.0233 1.0000
11.000 1.2054 0.03758 0.03018 -0.0022 0.0228 1.0000
11.250 1.2128 0.03959 0.03236 -0.0002 0.0222 1.0000
11.500 1.2199 0.04176 0.03472 0.0017 0.0221 1.0000
11.750 1.2231 0.04421 0.03739 0.0038 0.0217 1.0000
12.000 1.2248 0.04710 0.04053 0.0057 0.0219 1.0000
12.250 1.2219 0.05009 0.04378 0.0076 0.0220 1.0000
12.500 1.2158 0.05353 0.04748 0.0091 0.0224 1.0000
12.750 1.2069 0.05712 0.05131 0.0102 0.0226 1.0000
13.000 1.1948 0.06121 0.05564 0.0107 0.0229 1.0000
13.250 1.1805 0.06571 0.06037 0.0105 0.0231 1.0000
13.500 1.1642 0.07067 0.06555 0.0095 0.0232 1.0000
13.750 1.1473 0.07615 0.07123 0.0079 0.0235 1.0000
14.000 1.1289 0.08206 0.07732 0.0056 0.0237 1.0000
14.250 1.1205 0.08766 0.08303 0.0048 0.0245 1.0000
14.500 1.1037 0.09337 0.08891 0.0016 0.0246 1.0000
14.750 1.0901 0.09877 0.09447 -0.0018 0.0248 1.0000
15.000 1.0716 0.10560 0.10149 -0.0064 0.0251 1.0000
15.250 1.0478 0.11426 0.11031 -0.0121 0.0253 1.0000
15.500 1.0226 0.12404 0.12025 -0.0186 0.0255 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Fage & Collins 2 (fg2-il)