GOE 400 AIRFOIL (goe400-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 400 AIRFOIL (goe400-il) Reynolds number: 500,000 Max Cl/Cd: 109.77 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe400-il-500000.txt Download as CSV file: xf-goe400-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 400 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4333 0.11319 0.11096 0.0057 1.0000 0.0215
-9.000 -0.4302 0.11006 0.10784 0.0024 1.0000 0.0216
-8.750 -0.4250 0.10670 0.10450 -0.0001 1.0000 0.0217
-8.500 -0.4190 0.10318 0.10100 -0.0023 1.0000 0.0217
-8.250 -0.4119 0.09828 0.09612 -0.0011 1.0000 0.0222
-8.000 -0.4024 0.09553 0.09338 -0.0016 1.0000 0.0226
-7.750 -0.3936 0.09285 0.09072 -0.0026 1.0000 0.0230
-7.500 -0.3852 0.09008 0.08797 -0.0042 1.0000 0.0236
-7.250 -0.3758 0.08712 0.08503 -0.0064 1.0000 0.0245
-7.000 -0.3629 0.08367 0.08158 -0.0102 1.0000 0.0258
-6.750 -0.3378 0.07898 0.07688 -0.0228 1.0000 0.0275
-6.500 -0.3180 0.07467 0.07255 -0.0283 1.0000 0.0276
-6.250 -0.3098 0.06883 0.06673 -0.0311 1.0000 0.0283
-6.000 -0.2961 0.06657 0.06449 -0.0310 1.0000 0.0288
-5.750 -0.2775 0.06407 0.06200 -0.0328 0.9978 0.0295
-5.500 -0.2411 0.06032 0.05820 -0.0397 0.9834 0.0312
-5.250 -0.1802 0.05451 0.05220 -0.0548 0.9619 0.0351
-5.000 -0.1548 0.04766 0.04522 -0.0608 0.9349 0.0363
-4.750 -0.1352 0.04593 0.04339 -0.0608 0.8999 0.0371
-4.500 -0.1142 0.04414 0.04144 -0.0611 0.8645 0.0383
-4.250 -0.0881 0.04183 0.03892 -0.0630 0.8332 0.0407
-4.000 -0.0438 0.03463 0.03127 -0.0709 0.8102 0.0458
-3.750 -0.0210 0.03331 0.02980 -0.0710 0.7880 0.0468
-3.500 0.0041 0.03199 0.02834 -0.0714 0.7692 0.0481
-3.250 0.0460 0.02088 0.01630 -0.0771 0.7583 0.0461
-3.000 0.0753 0.01416 0.00859 -0.0784 0.7462 0.0401
-2.750 0.1029 0.01282 0.00689 -0.0782 0.7330 0.0403
-2.500 0.1306 0.01206 0.00589 -0.0780 0.7208 0.0410
-2.250 0.1582 0.01148 0.00511 -0.0778 0.7097 0.0420
-2.000 0.1859 0.01092 0.00436 -0.0775 0.6991 0.0427
-1.750 0.2138 0.01048 0.00380 -0.0773 0.6887 0.0434
-1.500 0.2415 0.01015 0.00336 -0.0770 0.6793 0.0441
-1.250 0.2692 0.00990 0.00301 -0.0768 0.6699 0.0447
-1.000 0.2970 0.00945 0.00249 -0.0765 0.6607 0.0463
-0.750 0.3246 0.00922 0.00221 -0.0763 0.6521 0.0488
-0.500 0.3526 0.00905 0.00202 -0.0761 0.6429 0.0526
-0.250 0.3804 0.00891 0.00185 -0.0758 0.6344 0.0584
0.000 0.4084 0.00895 0.00200 -0.0756 0.6254 0.0862
0.250 0.4367 0.00921 0.00222 -0.0754 0.6166 0.1010
0.500 0.4644 0.00928 0.00223 -0.0752 0.6081 0.1080
0.750 0.4923 0.00931 0.00227 -0.0751 0.5986 0.1138
1.000 0.5199 0.00932 0.00224 -0.0749 0.5882 0.1188
1.250 0.5473 0.00929 0.00220 -0.0747 0.5775 0.1250
1.500 0.5751 0.00928 0.00219 -0.0745 0.5667 0.1290
1.750 0.6027 0.00924 0.00214 -0.0743 0.5566 0.1327
2.000 0.6301 0.00919 0.00210 -0.0741 0.5455 0.1380
2.250 0.6575 0.00920 0.00208 -0.0739 0.5325 0.1409
2.500 0.6850 0.00920 0.00207 -0.0737 0.5190 0.1424
2.750 0.7126 0.00922 0.00208 -0.0735 0.5068 0.1439
3.000 0.7401 0.00926 0.00212 -0.0734 0.4951 0.1454
3.250 0.7675 0.00929 0.00215 -0.0732 0.4830 0.1484
3.500 0.7949 0.00935 0.00222 -0.0730 0.4701 0.1522
3.750 0.8221 0.00944 0.00231 -0.0728 0.4560 0.1574
4.000 0.8493 0.00952 0.00242 -0.0726 0.4429 0.1696
4.250 0.8686 0.00824 0.00267 -0.0711 0.4309 0.8867
4.500 0.9020 0.00833 0.00278 -0.0722 0.4162 1.0000
4.750 0.9289 0.00852 0.00293 -0.0720 0.4015 1.0000
5.000 0.9557 0.00873 0.00310 -0.0717 0.3870 1.0000
5.250 0.9824 0.00895 0.00328 -0.0715 0.3716 1.0000
5.500 1.0087 0.00922 0.00347 -0.0712 0.3499 1.0000
5.750 1.0346 0.00955 0.00371 -0.0709 0.3258 1.0000
6.000 1.0604 0.00989 0.00397 -0.0706 0.2999 1.0000
6.250 1.0856 0.01032 0.00427 -0.0703 0.2692 1.0000
6.500 1.1103 0.01083 0.00462 -0.0699 0.2321 1.0000
6.750 1.1339 0.01152 0.00509 -0.0694 0.1880 1.0000
7.000 1.1563 0.01240 0.00568 -0.0689 0.1383 1.0000
7.250 1.1786 0.01326 0.00631 -0.0684 0.1005 1.0000
7.500 1.2022 0.01388 0.00687 -0.0679 0.0849 1.0000
7.750 1.2243 0.01472 0.00755 -0.0672 0.0513 1.0000
8.000 1.2437 0.01597 0.00859 -0.0663 0.0269 1.0000
8.250 1.2662 0.01672 0.00942 -0.0655 0.0236 1.0000
8.500 1.2881 0.01748 0.01025 -0.0647 0.0216 1.0000
8.750 1.3072 0.01861 0.01146 -0.0637 0.0196 1.0000
9.000 1.3267 0.01959 0.01254 -0.0626 0.0185 1.0000
9.250 1.3470 0.02041 0.01344 -0.0617 0.0175 1.0000
9.500 1.3654 0.02139 0.01450 -0.0606 0.0166 1.0000
9.750 1.3822 0.02249 0.01567 -0.0594 0.0158 1.0000
10.000 1.3960 0.02384 0.01709 -0.0579 0.0152 1.0000
10.250 1.4029 0.02582 0.01919 -0.0556 0.0146 1.0000
10.500 1.4099 0.02773 0.02121 -0.0534 0.0142 1.0000
10.750 1.4216 0.02887 0.02246 -0.0515 0.0139 1.0000
11.000 1.4305 0.03015 0.02385 -0.0495 0.0136 1.0000
11.250 1.4380 0.03158 0.02539 -0.0477 0.0131 1.0000
11.500 1.4444 0.03319 0.02709 -0.0460 0.0127 1.0000
11.750 1.4501 0.03497 0.02897 -0.0446 0.0123 1.0000
12.000 1.4545 0.03699 0.03112 -0.0434 0.0120 1.0000
12.250 1.4584 0.03918 0.03340 -0.0424 0.0118 1.0000
12.500 1.4615 0.04154 0.03587 -0.0416 0.0116 1.0000
12.750 1.4636 0.04409 0.03852 -0.0409 0.0114 1.0000
13.000 1.4645 0.04686 0.04139 -0.0402 0.0112 1.0000
13.250 1.4638 0.04992 0.04456 -0.0394 0.0110 1.0000
13.500 1.4608 0.05343 0.04821 -0.0385 0.0108 1.0000
13.750 1.4551 0.05739 0.05235 -0.0378 0.0107 1.0000
14.000 1.4452 0.06205 0.05722 -0.0374 0.0106 1.0000
14.250 1.4337 0.06682 0.06218 -0.0379 0.0106 1.0000
14.500 1.4233 0.07142 0.06697 -0.0392 0.0105 1.0000
14.750 1.4115 0.07632 0.07205 -0.0408 0.0105 1.0000
15.000 1.3980 0.08169 0.07760 -0.0427 0.0105 1.0000
15.250 1.3834 0.08747 0.08355 -0.0450 0.0105 1.0000
15.500 1.3679 0.09369 0.08996 -0.0478 0.0105 1.0000
15.750 1.3513 0.10047 0.09691 -0.0509 0.0105 1.0000
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