GOE 400 AIRFOIL (goe400-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 400 AIRFOIL (goe400-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.02 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe400-il-1000000.txt Download as CSV file: xf-goe400-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4170 0.09698 0.09545 -0.0001 1.0000 0.0169
-8.000 -0.4112 0.09335 0.09183 -0.0025 1.0000 0.0170
-7.750 -0.4050 0.08951 0.08801 -0.0053 1.0000 0.0170
-7.500 -0.3945 0.08518 0.08368 -0.0095 1.0000 0.0171
-7.250 -0.3867 0.08084 0.07936 -0.0121 1.0000 0.0176
-7.000 -0.3712 0.07867 0.07720 -0.0139 1.0000 0.0179
-6.750 -0.3546 0.07613 0.07465 -0.0166 1.0000 0.0185
-6.500 -0.3356 0.07301 0.07153 -0.0206 0.9965 0.0195
-6.250 -0.2927 0.06574 0.06418 -0.0351 0.9643 0.0216
-6.000 -0.2442 0.04248 0.04056 -0.0395 0.8173 0.0222
-5.750 -0.2264 0.04045 0.03840 -0.0407 0.7889 0.0226
-5.500 -0.2068 0.03867 0.03652 -0.0419 0.7669 0.0232
-5.250 -0.1850 0.03609 0.03385 -0.0445 0.7490 0.0243
-5.000 -0.1692 0.04762 0.04521 -0.0551 0.7823 0.0274
-4.500 -0.0919 0.01638 0.01228 -0.0772 0.7560 0.0271
-4.250 -0.0644 0.01580 0.01148 -0.0771 0.7388 0.0275
-4.000 -0.0383 0.01244 0.00748 -0.0777 0.7252 0.0286
-3.750 -0.0110 0.01164 0.00650 -0.0777 0.7121 0.0293
-3.500 0.0165 0.01104 0.00575 -0.0775 0.6999 0.0298
-3.250 0.0443 0.01051 0.00508 -0.0774 0.6888 0.0301
-3.000 0.0721 0.01005 0.00448 -0.0772 0.6786 0.0305
-2.500 0.1279 0.00927 0.00350 -0.0769 0.6594 0.0315
-2.250 0.1558 0.00899 0.00314 -0.0767 0.6507 0.0323
-2.000 0.1838 0.00874 0.00281 -0.0766 0.6418 0.0332
-1.750 0.2118 0.00850 0.00250 -0.0764 0.6337 0.0339
-1.500 0.2398 0.00832 0.00225 -0.0762 0.6251 0.0345
-1.250 0.2678 0.00816 0.00205 -0.0761 0.6172 0.0349
-1.000 0.2958 0.00804 0.00187 -0.0759 0.6090 0.0352
-0.750 0.3239 0.00777 0.00154 -0.0757 0.6010 0.0363
-0.250 0.3800 0.00750 0.00120 -0.0754 0.5847 0.0406
0.000 0.4079 0.00744 0.00111 -0.0752 0.5764 0.0438
0.250 0.4359 0.00731 0.00103 -0.0751 0.5659 0.0631
0.500 0.4640 0.00745 0.00122 -0.0749 0.5550 0.0908
0.750 0.4920 0.00750 0.00127 -0.0748 0.5455 0.0973
1.000 0.5200 0.00758 0.00132 -0.0747 0.5343 0.1013
1.250 0.5479 0.00767 0.00138 -0.0745 0.5223 0.1035
1.500 0.5757 0.00763 0.00132 -0.0744 0.5099 0.1070
1.750 0.6035 0.00766 0.00133 -0.0743 0.4964 0.1102
2.000 0.6312 0.00773 0.00138 -0.0741 0.4839 0.1143
2.250 0.6589 0.00779 0.00140 -0.0740 0.4719 0.1159
2.750 0.7143 0.00786 0.00142 -0.0737 0.4465 0.1202
3.000 0.7420 0.00791 0.00146 -0.0736 0.4343 0.1215
3.250 0.7696 0.00798 0.00151 -0.0735 0.4217 0.1227
3.500 0.7970 0.00808 0.00157 -0.0733 0.4064 0.1240
3.750 0.8244 0.00818 0.00166 -0.0732 0.3925 0.1254
4.000 0.8518 0.00830 0.00175 -0.0731 0.3777 0.1270
4.250 0.8791 0.00843 0.00185 -0.0729 0.3629 0.1289
4.500 0.9063 0.00857 0.00197 -0.0728 0.3488 0.1311
4.750 0.9333 0.00873 0.00211 -0.0726 0.3310 0.1394
5.000 0.9599 0.00871 0.00238 -0.0726 0.3098 0.3469
5.250 0.9842 0.00781 0.00265 -0.0722 0.2844 1.0000
5.500 1.0103 0.00816 0.00287 -0.0719 0.2554 1.0000
5.750 1.0357 0.00863 0.00316 -0.0716 0.2177 1.0000
6.000 1.0602 0.00925 0.00353 -0.0713 0.1726 1.0000
6.250 1.0840 0.00998 0.00398 -0.0709 0.1231 1.0000
6.500 1.1085 0.01058 0.00441 -0.0705 0.0945 1.0000
6.750 1.1341 0.01093 0.00474 -0.0702 0.0850 1.0000
7.000 1.1594 0.01135 0.00511 -0.0699 0.0754 1.0000
7.250 1.1849 0.01170 0.00543 -0.0696 0.0645 1.0000
7.500 1.2064 0.01273 0.00617 -0.0689 0.0239 1.0000
7.750 1.2304 0.01332 0.00677 -0.0683 0.0188 1.0000
8.000 1.2551 0.01376 0.00725 -0.0679 0.0171 1.0000
8.250 1.2787 0.01436 0.00786 -0.0673 0.0152 1.0000
8.500 1.3020 0.01498 0.00855 -0.0667 0.0140 1.0000
8.750 1.3258 0.01547 0.00909 -0.0662 0.0133 1.0000
9.000 1.3489 0.01602 0.00969 -0.0656 0.0126 1.0000
9.250 1.3714 0.01664 0.01035 -0.0650 0.0119 1.0000
9.500 1.3917 0.01753 0.01131 -0.0641 0.0111 1.0000
9.750 1.4088 0.01877 0.01267 -0.0628 0.0105 1.0000
10.000 1.4307 0.01934 0.01330 -0.0621 0.0102 1.0000
10.250 1.4515 0.01998 0.01400 -0.0613 0.0098 1.0000
10.500 1.4713 0.02071 0.01478 -0.0604 0.0093 1.0000
10.750 1.4898 0.02152 0.01566 -0.0594 0.0090 1.0000
11.000 1.5071 0.02239 0.01658 -0.0583 0.0086 1.0000
11.250 1.5225 0.02339 0.01765 -0.0570 0.0083 1.0000
11.500 1.5321 0.02483 0.01917 -0.0551 0.0080 1.0000
11.750 1.5275 0.02706 0.02155 -0.0516 0.0077 1.0000
12.000 1.5270 0.02895 0.02356 -0.0490 0.0076 1.0000
12.250 1.5349 0.03031 0.02501 -0.0476 0.0075 1.0000
12.500 1.5405 0.03201 0.02681 -0.0464 0.0074 1.0000
12.750 1.5447 0.03402 0.02892 -0.0455 0.0073 1.0000
13.000 1.5477 0.03634 0.03135 -0.0450 0.0072 1.0000
13.250 1.5499 0.03888 0.03400 -0.0447 0.0071 1.0000
13.500 1.5507 0.04168 0.03693 -0.0446 0.0069 1.0000
13.750 1.5499 0.04475 0.04012 -0.0447 0.0068 1.0000
14.000 1.5486 0.04795 0.04342 -0.0449 0.0067 1.0000
14.250 1.5458 0.05139 0.04697 -0.0453 0.0066 1.0000
14.500 1.5411 0.05513 0.05083 -0.0458 0.0065 1.0000
14.750 1.5367 0.05888 0.05470 -0.0465 0.0064 1.0000
15.000 1.5308 0.06293 0.05885 -0.0473 0.0064 1.0000
15.250 1.5239 0.06717 0.06321 -0.0484 0.0063 1.0000
15.500 1.5172 0.07152 0.06766 -0.0496 0.0062 1.0000
15.750 1.5094 0.07624 0.07248 -0.0511 0.0061 1.0000
16.000 1.5009 0.08115 0.07750 -0.0527 0.0061 1.0000
16.250 1.4920 0.08631 0.08275 -0.0546 0.0060 1.0000
16.500 1.4829 0.09163 0.08818 -0.0566 0.0059 1.0000
16.750 1.4726 0.09723 0.09388 -0.0588 0.0059 1.0000
17.000 1.4612 0.10312 0.09987 -0.0612 0.0058 1.0000
17.250 1.4493 0.10921 0.10607 -0.0638 0.0058 1.0000
17.500 1.4371 0.11548 0.11246 -0.0665 0.0058 1.0000
17.750 1.4246 0.12189 0.11896 -0.0694 0.0057 1.0000
18.000 1.4116 0.12855 0.12573 -0.0726 0.0057 1.0000
18.250 1.3983 0.13545 0.13275 -0.0760 0.0057 1.0000
18.500 1.3850 0.14253 0.13994 -0.0797 0.0056 1.0000
18.750 1.3717 0.14976 0.14728 -0.0837 0.0056 1.0000
19.000 1.3581 0.15737 0.15501 -0.0880 0.0056 1.0000
19.250 1.3446 0.16523 0.16299 -0.0927 0.0056 1.0000
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