Fage & Collins 3 (fg3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Fage & Collins 3 (fg3-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.88 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg3-il-1000000.txt Download as CSV file: xf-fg3-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 3
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3625 0.12702 0.12539 -0.0244 1.0000 0.0095
-11.250 -0.3594 0.12319 0.12158 -0.0241 1.0000 0.0097
-11.000 -0.3573 0.11980 0.11820 -0.0247 1.0000 0.0097
-10.750 -0.3521 0.11761 0.11603 -0.0245 1.0000 0.0099
-10.500 -0.3491 0.11489 0.11332 -0.0248 1.0000 0.0100
-10.250 -0.3472 0.11202 0.11046 -0.0251 1.0000 0.0100
-10.000 -0.3452 0.10953 0.10798 -0.0252 1.0000 0.0103
-9.750 -0.3384 0.10609 0.10455 -0.0271 0.9996 0.0104
-9.500 -0.3233 0.10199 0.10045 -0.0315 0.9983 0.0107
-9.250 -0.3118 0.09635 0.09481 -0.0388 0.9963 0.0124
-9.000 -0.2976 0.09133 0.08980 -0.0450 0.9945 0.0124
-8.750 -0.2860 0.08678 0.08525 -0.0496 0.9917 0.0124
-8.500 -0.2733 0.08183 0.08030 -0.0555 0.9883 0.0125
-8.250 -0.2589 0.07684 0.07531 -0.0626 0.9852 0.0125
-8.000 -0.2582 0.07290 0.07138 -0.0641 0.9762 0.0128
-7.750 -0.2563 0.06864 0.06711 -0.0670 0.9556 0.0128
-7.500 -0.2390 0.06515 0.06359 -0.0709 0.9467 0.0130
-7.250 -0.2156 0.06059 0.05897 -0.0772 0.9398 0.0132
-7.000 -0.1845 0.05658 0.05488 -0.0841 0.9351 0.0143
-6.750 -0.1416 0.04799 0.04601 -0.0958 0.9285 0.0159
-6.500 -0.1013 0.04151 0.03926 -0.1038 0.9219 0.0160
-6.000 -0.0504 0.03207 0.02933 -0.1106 0.9054 0.0166
-5.750 -0.0270 0.03120 0.02838 -0.1112 0.8971 0.0172
-5.500 -0.0084 0.02954 0.02658 -0.1104 0.8883 0.0182
-5.250 0.0125 0.02721 0.02385 -0.1075 0.8813 0.0203
-5.000 0.0244 0.02494 0.02131 -0.1045 0.8748 0.0203
-4.750 0.0233 0.02044 0.01642 -0.0994 0.8676 0.0209
-4.500 0.0434 0.01966 0.01562 -0.0985 0.8617 0.0213
-4.250 0.0611 0.01891 0.01481 -0.0967 0.8546 0.0219
-4.000 0.0827 0.01842 0.01424 -0.0956 0.8480 0.0237
-3.750 0.1064 0.01881 0.01438 -0.0934 0.8399 0.0258
-3.500 0.1246 0.01777 0.01312 -0.0912 0.8325 0.0259
-3.250 0.1346 0.01456 0.00957 -0.0875 0.8225 0.0267
-3.000 0.1552 0.01359 0.00858 -0.0861 0.8119 0.0275
-2.750 0.1761 0.01308 0.00801 -0.0847 0.7985 0.0287
-2.500 0.1970 0.01273 0.00753 -0.0830 0.7816 0.0308
-2.250 0.2184 0.01336 0.00801 -0.0812 0.7587 0.0328
-2.000 0.2375 0.01320 0.00765 -0.0790 0.7330 0.0330
-1.750 0.2559 0.01111 0.00533 -0.0770 0.7067 0.0352
-1.500 0.2747 0.01079 0.00489 -0.0750 0.6733 0.0366
-1.250 0.2922 0.01068 0.00460 -0.0727 0.6302 0.0386
-1.000 0.3077 0.01082 0.00448 -0.0699 0.5740 0.0408
-0.750 0.3237 0.01050 0.00393 -0.0675 0.5235 0.0466
-0.500 0.3427 0.01046 0.00374 -0.0656 0.4852 0.0499
-0.250 0.3647 0.01013 0.00315 -0.0637 0.4599 0.0342
0.000 0.3863 0.01020 0.00312 -0.0623 0.4381 0.0335
0.250 0.4070 0.01007 0.00292 -0.0607 0.4209 0.0335
0.500 0.4273 0.00989 0.00268 -0.0590 0.4064 0.0328
0.750 0.4471 0.00968 0.00241 -0.0573 0.3941 0.0325
1.000 0.4684 0.00962 0.00229 -0.0558 0.3831 0.0327
1.250 0.4902 0.00963 0.00224 -0.0545 0.3727 0.0331
1.500 0.5115 0.00953 0.00209 -0.0531 0.3632 0.0336
1.750 0.5334 0.00949 0.00200 -0.0518 0.3550 0.0346
2.000 0.5558 0.00951 0.00197 -0.0506 0.3476 0.0352
2.250 0.5782 0.00953 0.00196 -0.0495 0.3405 0.0359
2.500 0.6009 0.00957 0.00197 -0.0484 0.3341 0.0376
2.750 0.6230 0.00964 0.00201 -0.0473 0.3279 0.0393
3.000 0.6461 0.00967 0.00203 -0.0463 0.3229 0.0419
3.250 0.8987 0.00869 0.00309 -0.0995 0.3043 1.0000
3.500 0.9208 0.00885 0.00321 -0.0983 0.2993 1.0000
3.750 0.9443 0.00894 0.00331 -0.0975 0.2958 1.0000
4.000 0.9672 0.00905 0.00341 -0.0966 0.2916 1.0000
4.250 0.9887 0.00924 0.00355 -0.0954 0.2843 1.0000
4.500 1.0123 0.00932 0.00364 -0.0946 0.2792 1.0000
4.750 1.0344 0.00947 0.00377 -0.0936 0.2729 1.0000
5.000 1.0569 0.00961 0.00390 -0.0926 0.2675 1.0000
5.250 1.0796 0.00974 0.00403 -0.0916 0.2620 1.0000
5.500 1.1011 0.00993 0.00420 -0.0905 0.2562 1.0000
5.750 1.1239 0.01005 0.00433 -0.0896 0.2501 1.0000
6.000 1.1450 0.01026 0.00450 -0.0884 0.2414 1.0000
6.250 1.1669 0.01043 0.00466 -0.0874 0.2314 1.0000
6.500 1.1874 0.01067 0.00486 -0.0861 0.2182 1.0000
6.750 1.2025 0.01125 0.00519 -0.0839 0.1779 1.0000
7.250 1.2044 0.01435 0.00735 -0.0742 0.0183 1.0000
7.500 1.2227 0.01471 0.00776 -0.0725 0.0164 1.0000
7.750 1.2402 0.01510 0.00819 -0.0707 0.0152 1.0000
8.000 1.2555 0.01561 0.00875 -0.0685 0.0137 1.0000
8.250 1.2672 0.01619 0.00941 -0.0655 0.0126 1.0000
8.500 1.2801 0.01658 0.00985 -0.0627 0.0122 1.0000
8.750 1.2929 0.01698 0.01030 -0.0601 0.0117 1.0000
9.000 1.3047 0.01744 0.01082 -0.0572 0.0111 1.0000
9.250 1.3159 0.01796 0.01139 -0.0544 0.0104 1.0000
9.500 1.3257 0.01858 0.01206 -0.0514 0.0098 1.0000
9.750 1.3252 0.01974 0.01335 -0.0467 0.0092 1.0000
10.000 1.3265 0.02081 0.01453 -0.0425 0.0090 1.0000
10.250 1.3348 0.02157 0.01537 -0.0397 0.0090 1.0000
10.500 1.3468 0.02216 0.01601 -0.0375 0.0087 1.0000
10.750 1.3530 0.02310 0.01703 -0.0346 0.0085 1.0000
11.000 1.3552 0.02429 0.01832 -0.0314 0.0085 1.0000
11.250 1.3696 0.02485 0.01890 -0.0300 0.0077 1.0000
11.500 1.3742 0.02602 0.02015 -0.0275 0.0076 1.0000
11.750 1.3754 0.02748 0.02169 -0.0247 0.0073 1.0000
12.000 1.3791 0.02885 0.02313 -0.0226 0.0071 1.0000
12.250 1.3790 0.03058 0.02493 -0.0202 0.0069 1.0000
12.500 1.3775 0.03252 0.02697 -0.0181 0.0069 1.0000
12.750 1.3710 0.03505 0.02959 -0.0160 0.0068 1.0000
13.000 1.3652 0.03772 0.03238 -0.0143 0.0068 1.0000
13.250 1.3503 0.04153 0.03629 -0.0129 0.0065 1.0000
13.500 1.3376 0.04540 0.04028 -0.0120 0.0065 1.0000
13.750 1.3195 0.05008 0.04508 -0.0113 0.0064 1.0000
14.000 1.3222 0.05277 0.04787 -0.0117 0.0062 1.0000
14.250 1.3170 0.05642 0.05162 -0.0118 0.0061 1.0000
14.500 1.3105 0.06017 0.05546 -0.0120 0.0062 1.0000
14.750 1.3082 0.06369 0.05908 -0.0126 0.0061 1.0000
15.000 1.3031 0.06738 0.06286 -0.0129 0.0061 1.0000
15.250 1.3067 0.07079 0.06637 -0.0147 0.0056 1.0000
15.500 1.2966 0.07467 0.07034 -0.0141 0.0059 1.0000
15.750 1.2926 0.07820 0.07394 -0.0143 0.0059 1.0000
16.000 1.2899 0.08215 0.07799 -0.0158 0.0057 1.0000
16.250 1.2860 0.08562 0.08155 -0.0158 0.0058 1.0000
16.500 1.2822 0.08978 0.08580 -0.0173 0.0055 1.0000
16.750 1.2785 0.09338 0.08950 -0.0177 0.0055 1.0000
17.000 1.2743 0.09752 0.09372 -0.0191 0.0053 1.0000
17.250 1.2697 0.10149 0.09779 -0.0199 0.0052 1.0000
17.500 1.2660 0.10572 0.10209 -0.0217 0.0051 1.0000
17.750 1.2617 0.10976 0.10623 -0.0228 0.0051 1.0000
18.000 1.2579 0.11422 0.11074 -0.0250 0.0049 1.0000
18.250 1.2527 0.11825 0.11489 -0.0259 0.0050 1.0000
18.500 1.2475 0.12292 0.11962 -0.0281 0.0048 1.0000
18.750 1.2430 0.12743 0.12421 -0.0301 0.0047 1.0000
19.000 1.2355 0.13218 0.12908 -0.0318 0.0047 1.0000
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Polar data table (+)
Polar graphs
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