GOE 380 AIRFOIL (goe380-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 380 AIRFOIL (goe380-il) Reynolds number: 200,000 Max Cl/Cd: 75.58 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe380-il-200000.txt Download as CSV file: xf-goe380-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 380 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.3092 0.08868 0.08570 -0.0214 1.0000 0.0226
-6.500 -0.3107 0.08609 0.08316 -0.0194 1.0000 0.0230
-6.250 -0.3138 0.08399 0.08108 -0.0178 1.0000 0.0233
-6.000 -0.3175 0.08204 0.07918 -0.0162 1.0000 0.0237
-5.750 -0.3205 0.08017 0.07736 -0.0150 1.0000 0.0241
-5.500 -0.2950 0.07627 0.07344 -0.0205 0.9961 0.0249
-5.250 -0.2606 0.07186 0.06897 -0.0278 0.9904 0.0265
-5.000 -0.2217 0.06744 0.06448 -0.0359 0.9848 0.0282
-4.750 -0.1640 0.06422 0.06107 -0.0482 0.9774 0.0310
-4.500 -0.1131 0.06091 0.05754 -0.0568 0.9717 0.0314
-4.250 -0.0939 0.05416 0.05084 -0.0596 0.9657 0.0326
-4.000 -0.0649 0.05034 0.04698 -0.0627 0.9593 0.0345
-3.750 -0.0193 0.04654 0.04304 -0.0689 0.9555 0.0387
-3.500 0.0348 0.04373 0.03982 -0.0751 0.9457 0.0435
-3.250 0.0682 0.03901 0.03516 -0.0790 0.9417 0.0463
-3.000 0.1021 0.03624 0.03224 -0.0811 0.9310 0.0501
-2.750 0.1532 0.03610 0.03149 -0.0834 0.9209 0.0555
-2.500 0.1786 0.03060 0.02604 -0.0855 0.9126 0.0577
-2.250 0.2071 0.02824 0.02357 -0.0861 0.9005 0.0607
-2.000 0.2458 0.02843 0.02316 -0.0858 0.8870 0.0686
-1.750 0.2699 0.02434 0.01901 -0.0860 0.8728 0.0705
-1.500 0.2961 0.02238 0.01693 -0.0857 0.8563 0.0745
-1.250 0.3278 0.01945 0.01338 -0.0841 0.8397 0.0530
-0.750 0.3847 0.01470 0.00753 -0.0815 0.8041 0.0434
-0.500 0.4107 0.01382 0.00648 -0.0806 0.7832 0.0487
-0.250 0.4369 0.01310 0.00551 -0.0796 0.7620 0.0575
0.000 0.4625 0.01278 0.00507 -0.0786 0.7401 0.0745
0.250 0.4877 0.01264 0.00475 -0.0778 0.7192 0.1018
0.500 0.5123 0.01238 0.00438 -0.0771 0.6992 0.1221
0.750 0.5370 0.01214 0.00404 -0.0762 0.6802 0.1328
1.000 0.5610 0.01185 0.00371 -0.0753 0.6626 0.1411
1.250 0.5853 0.01173 0.00351 -0.0744 0.6455 0.1500
1.500 0.6098 0.01168 0.00339 -0.0736 0.6291 0.1636
1.750 0.6342 0.01162 0.00336 -0.0728 0.6137 0.2019
2.000 0.7045 0.01023 0.00336 -0.0821 0.5937 1.0000
2.250 0.7284 0.01047 0.00343 -0.0812 0.5783 1.0000
2.500 0.7521 0.01072 0.00350 -0.0803 0.5627 1.0000
2.750 0.7756 0.01095 0.00361 -0.0793 0.5461 1.0000
3.000 0.7988 0.01119 0.00374 -0.0783 0.5290 1.0000
3.250 0.8220 0.01142 0.00387 -0.0773 0.5127 1.0000
3.500 0.8454 0.01167 0.00406 -0.0764 0.4977 1.0000
3.750 0.8690 0.01191 0.00424 -0.0756 0.4838 1.0000
4.000 0.8925 0.01215 0.00442 -0.0747 0.4702 1.0000
4.250 0.9159 0.01239 0.00462 -0.0738 0.4569 1.0000
4.500 0.9394 0.01263 0.00482 -0.0730 0.4444 1.0000
4.750 0.9628 0.01289 0.00508 -0.0721 0.4327 1.0000
5.000 0.9862 0.01316 0.00531 -0.0713 0.4215 1.0000
5.250 1.0095 0.01340 0.00557 -0.0705 0.4096 1.0000
5.500 1.0326 0.01367 0.00586 -0.0696 0.3980 1.0000
5.750 1.0558 0.01397 0.00617 -0.0688 0.3871 1.0000
6.000 1.0787 0.01431 0.00654 -0.0679 0.3767 1.0000
6.250 1.1014 0.01467 0.00688 -0.0670 0.3658 1.0000
6.500 1.1239 0.01500 0.00728 -0.0661 0.3539 1.0000
6.750 1.1457 0.01536 0.00768 -0.0651 0.3408 1.0000
7.000 1.1654 0.01569 0.00802 -0.0637 0.3220 1.0000
7.250 1.1854 0.01597 0.00838 -0.0624 0.3028 1.0000
7.500 1.2042 0.01631 0.00870 -0.0610 0.2816 1.0000
7.750 1.2238 0.01659 0.00905 -0.0597 0.2562 1.0000
8.000 1.2411 0.01707 0.00943 -0.0581 0.2149 1.0000
8.250 1.2479 0.01861 0.01037 -0.0551 0.1346 1.0000
8.500 1.2434 0.02128 0.01229 -0.0508 0.0372 1.0000
8.750 1.2525 0.02272 0.01386 -0.0478 0.0300 1.0000
9.000 1.2638 0.02386 0.01522 -0.0452 0.0278 1.0000
9.250 1.2716 0.02510 0.01666 -0.0423 0.0253 1.0000
9.500 1.2727 0.02651 0.01822 -0.0385 0.0232 1.0000
9.750 1.2712 0.02808 0.01994 -0.0347 0.0223 1.0000
10.000 1.2669 0.02994 0.02191 -0.0310 0.0217 1.0000
10.250 1.2581 0.03236 0.02444 -0.0273 0.0210 1.0000
10.500 1.2539 0.03478 0.02694 -0.0246 0.0206 1.0000
10.750 1.2538 0.03734 0.02956 -0.0222 0.0204 1.0000
11.000 1.2619 0.03955 0.03183 -0.0204 0.0201 1.0000
11.250 1.2761 0.04171 0.03410 -0.0189 0.0200 1.0000
11.500 1.2878 0.04380 0.03635 -0.0175 0.0197 1.0000
11.750 1.2928 0.04576 0.03849 -0.0161 0.0190 1.0000
12.000 1.3010 0.04813 0.04105 -0.0149 0.0187 1.0000
12.250 1.3083 0.05090 0.04403 -0.0136 0.0184 1.0000
12.500 1.3145 0.05434 0.04772 -0.0123 0.0187 1.0000
12.750 1.3174 0.05831 0.05195 -0.0113 0.0192 1.0000
13.000 1.3420 0.06223 0.05604 -0.0104 0.0210 1.0000
13.250 1.3311 0.06429 0.05837 -0.0092 0.0219 1.0000
13.500 1.3100 0.06854 0.06310 -0.0090 0.0238 1.0000
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Polar data table (+)
Polar graphs
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