GOE 269 AIRFOIL (goe269-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 269 AIRFOIL (goe269-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.9 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe269-il-1000000.txt Download as CSV file: xf-goe269-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 269 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3834 0.10139 0.09979 -0.0107 1.0000 0.0172
-8.500 -0.3782 0.09783 0.09624 -0.0126 1.0000 0.0172
-8.250 -0.3756 0.09359 0.09201 -0.0137 1.0000 0.0175
-8.000 -0.3657 0.09151 0.08995 -0.0141 1.0000 0.0177
-7.750 -0.3571 0.08941 0.08786 -0.0149 1.0000 0.0181
-7.500 -0.3479 0.08700 0.08547 -0.0164 1.0000 0.0185
-6.500 -0.2643 0.06728 0.06568 -0.0446 0.9627 0.0217
-6.250 -0.2436 0.06526 0.06360 -0.0463 0.9397 0.0220
-6.000 -0.2238 0.06297 0.06123 -0.0485 0.9192 0.0225
-5.750 -0.2016 0.06025 0.05842 -0.0517 0.9028 0.0234
-5.500 -0.1592 0.05435 0.05234 -0.0628 0.8886 0.0259
-5.250 -0.1310 0.04737 0.04520 -0.0700 0.8758 0.0264
-5.000 -0.1086 0.04560 0.04336 -0.0710 0.8610 0.0268
-4.750 -0.0842 0.04383 0.04150 -0.0724 0.8442 0.0272
-4.500 -0.0573 0.04178 0.03934 -0.0744 0.8255 0.0280
-4.250 -0.0153 0.03806 0.03536 -0.0795 0.8064 0.0314
-3.250 0.1212 0.01232 0.00737 -0.0938 0.7400 0.0314
-3.000 0.1506 0.01051 0.00512 -0.0943 0.7254 0.0323
-2.750 0.1792 0.01000 0.00448 -0.0945 0.7125 0.0333
-2.500 0.2079 0.00970 0.00409 -0.0945 0.7009 0.0340
-2.250 0.2366 0.00942 0.00372 -0.0945 0.6906 0.0346
-1.750 0.2941 0.00892 0.00306 -0.0946 0.6724 0.0361
-1.500 0.3227 0.00872 0.00277 -0.0946 0.6638 0.0370
-1.250 0.3516 0.00854 0.00256 -0.0947 0.6554 0.0378
-1.000 0.3803 0.00835 0.00229 -0.0947 0.6479 0.0388
-0.750 0.4092 0.00814 0.00207 -0.0948 0.6398 0.0414
-0.500 0.4378 0.00811 0.00202 -0.0948 0.6317 0.0434
-0.250 0.4665 0.00806 0.00195 -0.0948 0.6234 0.0455
0.000 0.4953 0.00795 0.00183 -0.0948 0.6157 0.0491
0.250 0.5238 0.00798 0.00187 -0.0948 0.6067 0.0529
0.500 0.5523 0.00805 0.00192 -0.0948 0.5975 0.0557
0.750 0.5809 0.00801 0.00187 -0.0948 0.5856 0.0606
1.000 0.6092 0.00809 0.00192 -0.0948 0.5717 0.0643
1.250 0.6374 0.00818 0.00198 -0.0947 0.5554 0.0666
1.500 0.6659 0.00810 0.00185 -0.0948 0.5359 0.0706
1.750 0.6940 0.00818 0.00185 -0.0948 0.5109 0.0736
2.000 0.7218 0.00833 0.00189 -0.0948 0.4800 0.0767
2.250 0.7493 0.00854 0.00197 -0.0947 0.4507 0.0789
2.500 0.7773 0.00862 0.00197 -0.0947 0.4298 0.0818
2.750 0.8053 0.00869 0.00201 -0.0947 0.4150 0.0854
3.000 0.8333 0.00879 0.00207 -0.0947 0.4035 0.0883
3.250 0.8614 0.00887 0.00213 -0.0947 0.3932 0.0910
3.500 0.8894 0.00895 0.00220 -0.0947 0.3837 0.0936
3.750 0.9173 0.00905 0.00230 -0.0947 0.3740 0.1014
4.000 0.9453 0.00910 0.00240 -0.0947 0.3651 0.1218
4.250 0.9683 0.00772 0.00269 -0.0941 0.3561 1.0000
4.500 0.9960 0.00789 0.00280 -0.0941 0.3452 1.0000
4.750 1.0238 0.00803 0.00292 -0.0940 0.3355 1.0000
5.000 1.0513 0.00822 0.00306 -0.0940 0.3236 1.0000
5.250 1.0785 0.00844 0.00321 -0.0939 0.3071 1.0000
5.500 1.1054 0.00870 0.00339 -0.0938 0.2869 1.0000
5.750 1.1321 0.00900 0.00359 -0.0936 0.2646 1.0000
6.000 1.1579 0.00943 0.00385 -0.0934 0.2311 1.0000
6.250 1.1827 0.01001 0.00421 -0.0931 0.1908 1.0000
6.500 1.2075 0.01058 0.00460 -0.0928 0.1591 1.0000
6.750 1.2328 0.01103 0.00495 -0.0925 0.1413 1.0000
7.000 1.2586 0.01138 0.00525 -0.0923 0.1302 1.0000
7.250 1.2844 0.01171 0.00556 -0.0920 0.1208 1.0000
7.500 1.3098 0.01208 0.00589 -0.0917 0.1114 1.0000
7.750 1.3352 0.01243 0.00621 -0.0914 0.1022 1.0000
8.000 1.3605 0.01278 0.00654 -0.0911 0.0926 1.0000
8.250 1.3848 0.01325 0.00693 -0.0907 0.0781 1.0000
8.500 1.4067 0.01403 0.00752 -0.0900 0.0538 1.0000
8.750 1.4252 0.01523 0.00848 -0.0888 0.0236 1.0000
9.000 1.4466 0.01599 0.00921 -0.0880 0.0175 1.0000
9.250 1.4694 0.01653 0.00980 -0.0873 0.0159 1.0000
9.500 1.4914 0.01714 0.01044 -0.0865 0.0147 1.0000
9.750 1.5117 0.01792 0.01128 -0.0854 0.0134 1.0000
10.000 1.5323 0.01861 0.01204 -0.0844 0.0127 1.0000
10.250 1.5532 0.01922 0.01271 -0.0835 0.0122 1.0000
10.500 1.5730 0.01989 0.01344 -0.0825 0.0116 1.0000
10.750 1.5918 0.02061 0.01421 -0.0813 0.0111 1.0000
11.000 1.6081 0.02151 0.01518 -0.0798 0.0105 1.0000
11.250 1.6164 0.02305 0.01685 -0.0772 0.0099 1.0000
11.500 1.6323 0.02379 0.01765 -0.0756 0.0097 1.0000
11.750 1.6457 0.02461 0.01855 -0.0737 0.0095 1.0000
12.000 1.6548 0.02554 0.01956 -0.0712 0.0093 1.0000
12.250 1.6610 0.02661 0.02072 -0.0683 0.0090 1.0000
12.500 1.6667 0.02785 0.02205 -0.0658 0.0088 1.0000
12.750 1.6718 0.02927 0.02355 -0.0636 0.0086 1.0000
13.000 1.6759 0.03091 0.02529 -0.0617 0.0084 1.0000
13.250 1.6792 0.03275 0.02722 -0.0601 0.0082 1.0000
13.500 1.6811 0.03488 0.02944 -0.0587 0.0080 1.0000
13.750 1.6803 0.03743 0.03208 -0.0576 0.0079 1.0000
14.000 1.6760 0.04057 0.03534 -0.0568 0.0077 1.0000
14.250 1.6679 0.04437 0.03926 -0.0565 0.0076 1.0000
14.500 1.6553 0.04893 0.04397 -0.0565 0.0075 1.0000
14.750 1.6378 0.05425 0.04944 -0.0568 0.0074 1.0000
15.000 1.6276 0.05880 0.05411 -0.0573 0.0073 1.0000
15.250 1.6242 0.06255 0.05798 -0.0580 0.0072 1.0000
15.500 1.6187 0.06665 0.06219 -0.0587 0.0072 1.0000
15.750 1.6106 0.07129 0.06695 -0.0598 0.0071 1.0000
16.000 1.6030 0.07603 0.07181 -0.0611 0.0070 1.0000
16.250 1.5941 0.08108 0.07697 -0.0626 0.0070 1.0000
16.500 1.5837 0.08650 0.08250 -0.0643 0.0069 1.0000
16.750 1.5721 0.09222 0.08834 -0.0663 0.0069 1.0000
17.000 1.5608 0.09794 0.09417 -0.0683 0.0068 1.0000
17.250 1.5484 0.10393 0.10028 -0.0705 0.0068 1.0000
17.500 1.5362 0.10997 0.10643 -0.0729 0.0067 1.0000
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