GOE 328 AIRFOIL (goe328-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 328 AIRFOIL (goe328-il) Reynolds number: 200,000 Max Cl/Cd: 74.79 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe328-il-200000-n5.txt Download as CSV file: xf-goe328-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 328 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3816 0.10555 0.10198 -0.0190 1.0000 0.0315
-8.500 -0.3787 0.10251 0.09898 -0.0221 1.0000 0.0316
-8.250 -0.3759 0.09948 0.09599 -0.0253 1.0000 0.0317
-8.000 -0.3702 0.09608 0.09261 -0.0295 1.0000 0.0318
-7.750 -0.3629 0.09176 0.08833 -0.0325 1.0000 0.0319
-7.500 -0.3570 0.08762 0.08420 -0.0303 1.0000 0.0324
-7.250 -0.3484 0.08450 0.08111 -0.0299 1.0000 0.0328
-7.000 -0.3408 0.08163 0.07827 -0.0305 1.0000 0.0332
-6.750 -0.3303 0.07861 0.07528 -0.0325 0.9964 0.0338
-6.500 -0.3064 0.07464 0.07128 -0.0381 0.9841 0.0347
-6.250 -0.2808 0.07072 0.06731 -0.0442 0.9713 0.0364
-6.000 -0.2352 0.06581 0.06217 -0.0591 0.9551 0.0405
-5.750 -0.2025 0.06147 0.05762 -0.0659 0.9423 0.0408
-5.500 -0.1745 0.05761 0.05358 -0.0700 0.9297 0.0409
-5.250 -0.1488 0.05402 0.04980 -0.0728 0.9162 0.0410
-5.000 -0.1339 0.04892 0.04467 -0.0742 0.9023 0.0418
-4.750 -0.1169 0.04654 0.04227 -0.0742 0.8880 0.0427
-4.500 -0.0963 0.04442 0.04007 -0.0746 0.8746 0.0440
-4.250 -0.0723 0.04203 0.03753 -0.0758 0.8617 0.0455
-4.000 -0.0462 0.03948 0.03477 -0.0772 0.8490 0.0469
-3.750 -0.0081 0.03795 0.03265 -0.0791 0.8366 0.0518
-3.500 0.0185 0.03580 0.03020 -0.0796 0.8245 0.0519
-3.250 0.0427 0.03016 0.02437 -0.0806 0.8135 0.0399
-3.000 0.0708 0.02806 0.02196 -0.0810 0.8033 0.0401
-2.750 0.0985 0.02616 0.01977 -0.0813 0.7936 0.0402
-2.500 0.1257 0.02412 0.01751 -0.0817 0.7833 0.0391
-2.250 0.1538 0.02239 0.01551 -0.0820 0.7737 0.0383
-2.000 0.1822 0.02084 0.01366 -0.0820 0.7640 0.0378
-1.750 0.2110 0.01945 0.01200 -0.0821 0.7538 0.0374
-1.500 0.2396 0.01828 0.01055 -0.0821 0.7443 0.0374
-1.250 0.2681 0.01729 0.00931 -0.0820 0.7343 0.0376
-1.000 0.2965 0.01645 0.00827 -0.0819 0.7241 0.0379
-0.750 0.3246 0.01586 0.00748 -0.0817 0.7139 0.0389
-0.500 0.3527 0.01544 0.00689 -0.0815 0.7034 0.0401
-0.250 0.3807 0.01492 0.00625 -0.0814 0.6916 0.0405
0.000 0.4083 0.01443 0.00564 -0.0812 0.6777 0.0406
0.250 0.4357 0.01403 0.00513 -0.0809 0.6616 0.0408
0.500 0.4630 0.01358 0.00462 -0.0807 0.6453 0.0413
0.750 0.4904 0.01315 0.00416 -0.0805 0.6303 0.0422
1.000 0.5181 0.01288 0.00388 -0.0805 0.6167 0.0434
1.250 0.5458 0.01270 0.00368 -0.0804 0.6031 0.0449
1.500 0.5735 0.01259 0.00354 -0.0804 0.5883 0.0471
1.750 0.6011 0.01255 0.00345 -0.0803 0.5719 0.0509
2.000 0.6287 0.01250 0.00332 -0.0802 0.5539 0.0538
2.250 0.6561 0.01249 0.00325 -0.0801 0.5349 0.0587
2.500 0.6835 0.01251 0.00323 -0.0799 0.5151 0.0727
3.000 0.7308 0.01086 0.00337 -0.0782 0.4808 1.0000
3.250 0.7577 0.01109 0.00347 -0.0780 0.4657 1.0000
3.500 0.7846 0.01134 0.00361 -0.0779 0.4523 1.0000
3.750 0.8113 0.01160 0.00378 -0.0777 0.4403 1.0000
4.000 0.8380 0.01186 0.00397 -0.0776 0.4292 1.0000
4.250 0.8649 0.01211 0.00418 -0.0775 0.4187 1.0000
4.500 0.8916 0.01238 0.00442 -0.0773 0.4093 1.0000
4.750 0.9182 0.01265 0.00467 -0.0772 0.3997 1.0000
5.000 0.9448 0.01292 0.00493 -0.0770 0.3903 1.0000
5.250 0.9710 0.01323 0.00522 -0.0768 0.3814 1.0000
5.500 0.9976 0.01348 0.00552 -0.0767 0.3714 1.0000
5.750 1.0237 0.01377 0.00581 -0.0764 0.3597 1.0000
6.000 1.0495 0.01407 0.00612 -0.0762 0.3470 1.0000
6.250 1.0750 0.01439 0.00645 -0.0759 0.3338 1.0000
6.500 1.1002 0.01471 0.00676 -0.0756 0.3166 1.0000
6.750 1.1244 0.01510 0.00710 -0.0752 0.2943 1.0000
7.000 1.1482 0.01555 0.00750 -0.0748 0.2705 1.0000
7.250 1.1715 0.01606 0.00795 -0.0742 0.2487 1.0000
7.500 1.1937 0.01669 0.00847 -0.0736 0.2188 1.0000
7.750 1.2083 0.01818 0.00939 -0.0723 0.1208 1.0000
8.000 1.2207 0.02000 0.01083 -0.0706 0.0612 1.0000
8.250 1.2382 0.02110 0.01188 -0.0694 0.0457 1.0000
8.500 1.2567 0.02203 0.01287 -0.0683 0.0377 1.0000
8.750 1.2746 0.02294 0.01387 -0.0671 0.0325 1.0000
9.000 1.2897 0.02404 0.01500 -0.0656 0.0287 1.0000
9.250 1.3059 0.02496 0.01606 -0.0642 0.0261 1.0000
9.500 1.3194 0.02603 0.01723 -0.0625 0.0243 1.0000
9.750 1.3288 0.02733 0.01860 -0.0603 0.0229 1.0000
10.000 1.3342 0.02866 0.02003 -0.0576 0.0218 1.0000
10.250 1.3407 0.02996 0.02147 -0.0552 0.0208 1.0000
10.500 1.3467 0.03142 0.02303 -0.0531 0.0197 1.0000
10.750 1.3519 0.03304 0.02477 -0.0513 0.0188 1.0000
11.000 1.3554 0.03491 0.02674 -0.0497 0.0181 1.0000
11.250 1.3567 0.03711 0.02903 -0.0482 0.0176 1.0000
11.500 1.3553 0.03972 0.03172 -0.0469 0.0172 1.0000
11.750 1.3558 0.04226 0.03437 -0.0458 0.0168 1.0000
12.000 1.3583 0.04469 0.03694 -0.0448 0.0165 1.0000
12.250 1.3606 0.04720 0.03958 -0.0440 0.0161 1.0000
12.500 1.3628 0.04977 0.04229 -0.0433 0.0156 1.0000
12.750 1.3649 0.05240 0.04505 -0.0427 0.0151 1.0000
13.000 1.3667 0.05512 0.04791 -0.0423 0.0146 1.0000
13.250 1.3679 0.05795 0.05085 -0.0421 0.0142 1.0000
13.500 1.3683 0.06090 0.05391 -0.0420 0.0138 1.0000
13.750 1.3681 0.06397 0.05708 -0.0419 0.0135 1.0000
14.000 1.3673 0.06715 0.06036 -0.0418 0.0133 1.0000
14.250 1.3659 0.07041 0.06373 -0.0417 0.0130 1.0000
14.500 1.3639 0.07380 0.06722 -0.0415 0.0128 1.0000
14.750 1.3615 0.07743 0.07100 -0.0415 0.0126 1.0000
15.000 1.3578 0.08137 0.07515 -0.0421 0.0125 1.0000
15.250 1.3528 0.08564 0.07962 -0.0429 0.0124 1.0000
15.500 1.3465 0.09026 0.08445 -0.0440 0.0122 1.0000
15.750 1.3388 0.09524 0.08966 -0.0455 0.0121 1.0000
16.000 1.3294 0.10066 0.09529 -0.0475 0.0120 1.0000
16.250 1.3189 0.10646 0.10131 -0.0498 0.0120 1.0000
16.500 1.3069 0.11276 0.10782 -0.0527 0.0119 1.0000
16.750 1.2940 0.11946 0.11474 -0.0561 0.0118 1.0000
17.000 1.2798 0.12667 0.12215 -0.0600 0.0118 1.0000
17.250 1.2646 0.13443 0.13011 -0.0645 0.0117 1.0000
17.500 1.2484 0.14282 0.13870 -0.0696 0.0118 1.0000
17.750 1.2306 0.15208 0.14816 -0.0754 0.0118 1.0000
18.000 1.2111 0.16243 0.15867 -0.0822 0.0119 1.0000
18.250 1.1884 0.17460 0.17102 -0.0902 0.0120 1.0000
18.500 1.1583 0.19106 0.18762 -0.1007 0.0123 1.0000
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Polar data table (+)
Polar graphs
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