GOE 492 AIRFOIL (goe492-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 492 AIRFOIL (goe492-il) Reynolds number: 100,000 Max Cl/Cd: 57.42 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe492-il-100000-n5.txt Download as CSV file: xf-goe492-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 492 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4029 0.10145 0.09657 -0.0341 1.0000 0.0379
-8.250 -0.4040 0.09874 0.09393 -0.0346 1.0000 0.0380
-8.000 -0.4070 0.09596 0.09123 -0.0347 1.0000 0.0380
-7.500 -0.4016 0.08788 0.08320 -0.0311 1.0000 0.0264
-7.250 -0.4077 0.08541 0.08083 -0.0301 1.0000 0.0253
-7.000 -0.4115 0.08248 0.07798 -0.0302 1.0000 0.0242
-6.750 -0.4145 0.07944 0.07501 -0.0307 1.0000 0.0233
-6.500 -0.4163 0.07601 0.07165 -0.0320 1.0000 0.0223
-6.250 -0.4157 0.07197 0.06765 -0.0343 1.0000 0.0214
-6.000 -0.4090 0.06577 0.06143 -0.0399 1.0000 0.0198
-5.500 -0.3828 0.05593 0.05139 -0.0463 1.0000 0.0187
-5.250 -0.3657 0.05033 0.04563 -0.0499 0.9996 0.0185
-5.000 -0.3290 0.04291 0.03781 -0.0577 0.9957 0.0184
-4.500 -0.2592 0.03261 0.02650 -0.0678 0.9884 0.0216
-4.250 -0.2239 0.02843 0.02156 -0.0708 0.9851 0.0228
-4.000 -0.1893 0.02490 0.01727 -0.0726 0.9818 0.0244
-3.750 -0.1535 0.02231 0.01384 -0.0740 0.9791 0.0291
-3.500 -0.1213 0.02078 0.01211 -0.0752 0.9754 0.0347
-3.250 -0.0888 0.01956 0.01062 -0.0762 0.9712 0.0461
-3.000 -0.0543 0.01855 0.00933 -0.0778 0.9678 0.0621
-2.750 -0.0240 0.01775 0.00844 -0.0786 0.9628 0.0747
-2.500 0.0087 0.01705 0.00763 -0.0797 0.9581 0.0819
-2.250 0.0446 0.01656 0.00699 -0.0814 0.9546 0.0908
-2.000 0.0733 0.01610 0.00646 -0.0818 0.9480 0.1055
-1.750 0.1072 0.01538 0.00624 -0.0834 0.9436 0.2040
-1.500 0.1407 0.01524 0.00612 -0.0847 0.9386 0.2922
-1.250 0.1719 0.01502 0.00589 -0.0856 0.9321 0.3353
-1.000 0.2081 0.01443 0.00575 -0.0876 0.9284 0.4325
-0.750 0.2447 0.01303 0.00569 -0.0888 0.9246 1.0000
-0.500 0.2780 0.01306 0.00551 -0.0899 0.9177 1.0000
-0.250 0.3135 0.01307 0.00536 -0.0914 0.9120 1.0000
0.000 0.3447 0.01310 0.00527 -0.0921 0.9038 1.0000
0.250 0.3778 0.01310 0.00520 -0.0931 0.8966 1.0000
0.500 0.4103 0.01310 0.00513 -0.0939 0.8886 1.0000
0.750 0.4402 0.01312 0.00511 -0.0943 0.8793 1.0000
1.000 0.4752 0.01307 0.00506 -0.0955 0.8724 1.0000
1.250 0.5028 0.01312 0.00512 -0.0953 0.8615 1.0000
1.500 0.5315 0.01316 0.00518 -0.0954 0.8510 1.0000
1.750 0.5613 0.01317 0.00525 -0.0956 0.8411 1.0000
2.000 0.5924 0.01317 0.00535 -0.0960 0.8318 1.0000
2.250 0.6197 0.01323 0.00550 -0.0957 0.8195 1.0000
2.500 0.6478 0.01326 0.00563 -0.0954 0.8060 1.0000
2.750 0.6762 0.01326 0.00579 -0.0951 0.7909 1.0000
3.000 0.7042 0.01328 0.00595 -0.0948 0.7750 1.0000
3.250 0.7309 0.01336 0.00622 -0.0942 0.7577 1.0000
3.500 0.7574 0.01331 0.00630 -0.0931 0.7277 1.0000
3.750 0.7746 0.01349 0.00568 -0.0885 0.5700 1.0000
4.000 0.7730 0.01614 0.00627 -0.0832 0.1963 1.0000
4.250 0.7826 0.01864 0.00779 -0.0804 0.0396 1.0000
4.500 0.8021 0.01974 0.00905 -0.0787 0.0314 1.0000
4.750 0.8203 0.02089 0.01032 -0.0770 0.0255 1.0000
5.000 0.8379 0.02215 0.01177 -0.0750 0.0232 1.0000
5.250 0.8554 0.02362 0.01341 -0.0730 0.0215 1.0000
5.500 0.8748 0.02528 0.01509 -0.0715 0.0190 1.0000
5.750 0.8980 0.02769 0.01755 -0.0706 0.0172 1.0000
6.000 0.9251 0.02997 0.02007 -0.0698 0.0167 1.0000
6.250 0.9517 0.03260 0.02300 -0.0689 0.0164 1.0000
6.500 0.9760 0.03548 0.02626 -0.0677 0.0163 1.0000
6.750 0.9972 0.03855 0.02977 -0.0661 0.0162 1.0000
7.000 1.0155 0.04156 0.03325 -0.0642 0.0157 1.0000
7.250 1.0308 0.04471 0.03688 -0.0620 0.0150 1.0000
7.500 1.0431 0.04815 0.04086 -0.0596 0.0146 1.0000
7.750 1.0520 0.05188 0.04500 -0.0572 0.0148 1.0000
8.000 1.0576 0.05575 0.04925 -0.0547 0.0151 1.0000
8.250 1.0598 0.05974 0.05358 -0.0522 0.0154 1.0000
8.500 1.0588 0.06370 0.05783 -0.0497 0.0157 1.0000
8.750 1.0544 0.06768 0.06207 -0.0474 0.0161 1.0000
9.000 1.0468 0.07156 0.06616 -0.0451 0.0164 1.0000
9.250 1.0348 0.07521 0.06998 -0.0427 0.0166 1.0000
9.500 1.0197 0.07893 0.07384 -0.0406 0.0168 1.0000
9.750 1.0040 0.08297 0.07800 -0.0397 0.0170 1.0000
10.250 0.8574 0.08759 0.08329 -0.0360 0.0164 1.0000
10.500 0.8363 0.09408 0.08988 -0.0391 0.0164 1.0000
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Polar data table (+)
Polar graphs
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