GOE 627 AIRFOIL (goe627-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 627 AIRFOIL (goe627-il) Reynolds number: 50,000 Max Cl/Cd: 25.4 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe627-il-50000.txt Download as CSV file: xf-goe627-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 627 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3236 0.11169 0.10532 -0.0146 1.0000 0.3311
-8.500 -0.3121 0.10816 0.10184 -0.0128 1.0000 0.3401
-8.250 -0.3574 0.10905 0.10293 -0.0098 1.0000 0.3513
-8.000 -0.3184 0.10390 0.09773 -0.0086 1.0000 0.3620
-7.750 -0.3362 0.10231 0.09627 -0.0059 1.0000 0.3732
-7.500 -0.3572 0.10166 0.09575 -0.0025 1.0000 0.3874
-7.250 -0.3381 0.09774 0.09186 -0.0013 1.0000 0.3946
-7.000 -0.3630 0.09673 0.09099 0.0025 1.0000 0.4088
-6.750 -0.3511 0.09389 0.08819 0.0043 1.0000 0.4186
-6.500 -0.3597 0.09195 0.08635 0.0074 1.0000 0.4315
-5.750 -0.5944 0.06218 0.05545 -0.0095 1.0000 0.1720
-5.500 -0.5890 0.05868 0.05181 -0.0079 1.0000 0.1666
-5.250 -0.5886 0.05400 0.04632 -0.0063 1.0000 0.1555
-5.000 -0.5793 0.05124 0.04334 -0.0045 1.0000 0.1527
-4.750 -0.5697 0.04857 0.04032 -0.0027 1.0000 0.1500
-4.500 -0.5585 0.04639 0.03777 -0.0009 1.0000 0.1495
-4.250 -0.5460 0.04457 0.03561 0.0008 1.0000 0.1500
-4.000 -0.5322 0.04293 0.03363 0.0025 1.0000 0.1507
-3.750 -0.5173 0.04145 0.03183 0.0041 1.0000 0.1511
-3.500 -0.5014 0.04017 0.03026 0.0056 1.0000 0.1519
-3.250 -0.4849 0.03912 0.02892 0.0069 1.0000 0.1535
-3.000 -0.4684 0.03837 0.02787 0.0082 1.0000 0.1563
-2.750 -0.4325 0.03792 0.02741 0.0060 0.9932 0.1629
-2.500 -0.3721 0.03796 0.02718 0.0001 0.9739 0.1735
-2.250 -0.3116 0.03785 0.02721 -0.0058 0.9561 0.1928
-2.000 -0.0503 0.03701 0.02999 -0.0401 0.9469 1.0000
-1.750 -0.0069 0.03730 0.02984 -0.0445 0.9271 1.0000
-1.500 0.0386 0.03758 0.02976 -0.0488 0.9083 1.0000
-1.250 0.0755 0.03771 0.02960 -0.0514 0.8887 1.0000
-1.000 0.1077 0.03777 0.02941 -0.0528 0.8682 1.0000
-0.750 0.1451 0.03779 0.02921 -0.0548 0.8488 1.0000
-0.500 0.1858 0.03769 0.02889 -0.0570 0.8299 1.0000
-0.250 0.2278 0.03748 0.02847 -0.0592 0.8116 1.0000
0.000 0.2716 0.03710 0.02791 -0.0613 0.7937 1.0000
0.250 0.3154 0.03659 0.02724 -0.0631 0.7761 1.0000
0.500 0.3605 0.03590 0.02640 -0.0649 0.7589 1.0000
0.750 0.4068 0.03505 0.02542 -0.0666 0.7423 1.0000
1.000 0.4588 0.03406 0.02429 -0.0692 0.7258 1.0000
1.250 0.5135 0.03301 0.02312 -0.0722 0.7089 1.0000
1.500 0.5658 0.03195 0.02192 -0.0747 0.6915 1.0000
1.750 0.6142 0.03109 0.02093 -0.0768 0.6735 1.0000
2.000 0.6581 0.03048 0.02017 -0.0783 0.6550 1.0000
2.250 0.6960 0.03017 0.01970 -0.0790 0.6363 1.0000
2.500 0.7234 0.03030 0.01970 -0.0783 0.6186 1.0000
2.750 0.7450 0.03065 0.01993 -0.0769 0.6016 1.0000
3.000 0.7610 0.03124 0.02044 -0.0746 0.5857 1.0000
3.250 0.7756 0.03194 0.02106 -0.0723 0.5712 1.0000
3.500 0.7972 0.03251 0.02154 -0.0710 0.5583 1.0000
3.750 0.8316 0.03274 0.02160 -0.0716 0.5460 1.0000
4.000 0.8231 0.03425 0.02319 -0.0661 0.5343 1.0000
4.250 0.8410 0.03505 0.02392 -0.0644 0.5240 1.0000
4.500 0.8547 0.03599 0.02483 -0.0622 0.5140 1.0000
4.750 0.8550 0.03752 0.02637 -0.0582 0.5055 1.0000
5.000 0.8646 0.03876 0.02762 -0.0556 0.4973 1.0000
5.250 0.8722 0.04020 0.02905 -0.0528 0.4901 1.0000
5.500 0.8370 0.04326 0.03221 -0.0448 0.4832 1.0000
5.750 0.9066 0.04238 0.03116 -0.0498 0.4754 1.0000
6.000 0.7844 0.04941 0.03841 -0.0324 0.4709 1.0000
6.250 0.5739 0.06879 0.05783 -0.0218 0.4661 1.0000
6.500 0.5490 0.07441 0.06344 -0.0212 0.4651 1.0000
6.750 0.5323 0.07925 0.06828 -0.0209 0.4649 1.0000
7.000 0.5155 0.08411 0.07314 -0.0208 0.4668 1.0000
7.250 0.5092 0.08848 0.07751 -0.0212 0.4713 1.0000
7.500 0.5264 0.09178 0.08082 -0.0219 0.4751 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 627 AIRFOIL (goe627-il)