GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Reynolds number: 500,000 Max Cl/Cd: 91.01 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe314-il-500000-n5.txt Download as CSV file: xf-goe314-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 314 (HANSA-BRANDENBURG) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3286 0.09414 0.09183 -0.0226 1.0000 0.0164
-8.500 -0.3274 0.09121 0.08892 -0.0232 1.0000 0.0166
-8.250 -0.3330 0.08747 0.08522 -0.0242 1.0000 0.0176
-8.000 -0.3291 0.08594 0.08373 -0.0235 1.0000 0.0179
-7.750 -0.3206 0.08355 0.08135 -0.0251 0.9983 0.0183
-7.500 -0.3073 0.08014 0.07795 -0.0292 0.9867 0.0186
-7.000 -0.2669 0.07171 0.06948 -0.0414 0.9570 0.0196
-6.750 -0.2282 0.06373 0.06138 -0.0564 0.9384 0.0214
-6.500 -0.1874 0.06112 0.05870 -0.0628 0.9205 0.0220
-6.250 -0.1508 0.05731 0.05475 -0.0703 0.8941 0.0227
-6.000 -0.1277 0.05370 0.05095 -0.0745 0.8636 0.0229
-5.750 -0.1098 0.05062 0.04769 -0.0766 0.8402 0.0231
-5.500 -0.0915 0.04771 0.04463 -0.0782 0.8225 0.0236
-5.250 -0.0720 0.04450 0.04124 -0.0798 0.8066 0.0245
-5.000 -0.0519 0.04122 0.03777 -0.0810 0.7925 0.0247
-4.750 -0.0307 0.03785 0.03418 -0.0820 0.7792 0.0249
-4.500 -0.0089 0.03438 0.03047 -0.0825 0.7665 0.0251
-4.250 0.0126 0.03147 0.02732 -0.0825 0.7527 0.0260
-4.000 0.0346 0.03046 0.02621 -0.0822 0.7363 0.0263
-3.750 0.0570 0.02843 0.02397 -0.0819 0.7201 0.0265
-3.500 0.0799 0.02643 0.02175 -0.0814 0.7026 0.0267
-3.250 0.1029 0.02457 0.01964 -0.0808 0.6820 0.0269
-3.000 0.1260 0.02287 0.01767 -0.0801 0.6590 0.0272
-2.750 0.1493 0.02109 0.01559 -0.0792 0.6339 0.0274
-2.500 0.1728 0.01945 0.01362 -0.0783 0.6086 0.0278
-2.250 0.1965 0.01800 0.01184 -0.0773 0.5816 0.0285
-2.000 0.2202 0.01602 0.00945 -0.0762 0.5573 0.0289
-1.750 0.2445 0.01434 0.00734 -0.0752 0.5362 0.0296
-1.500 0.2695 0.01338 0.00609 -0.0745 0.5177 0.0302
-1.250 0.2951 0.01283 0.00532 -0.0739 0.5009 0.0305
-1.000 0.3207 0.01235 0.00466 -0.0733 0.4857 0.0308
-0.750 0.3464 0.01191 0.00412 -0.0728 0.4728 0.0314
-0.500 0.3725 0.01177 0.00392 -0.0724 0.4610 0.0320
-0.250 0.3985 0.01168 0.00377 -0.0719 0.4489 0.0328
0.000 0.4243 0.01152 0.00352 -0.0714 0.4360 0.0335
0.250 0.4502 0.01133 0.00326 -0.0709 0.4236 0.0342
0.500 0.4759 0.01118 0.00303 -0.0703 0.4114 0.0349
0.750 0.5016 0.01107 0.00286 -0.0698 0.4012 0.0357
1.000 0.5278 0.01097 0.00272 -0.0693 0.3928 0.0365
1.250 0.5536 0.01088 0.00259 -0.0688 0.3858 0.0372
1.500 0.5797 0.01077 0.00249 -0.0684 0.3782 0.0384
1.750 0.6056 0.01079 0.00249 -0.0679 0.3703 0.0399
2.000 0.6320 0.01078 0.00248 -0.0676 0.3627 0.0421
2.500 0.6841 0.01078 0.00244 -0.0667 0.3470 0.0459
2.750 0.7097 0.01084 0.00247 -0.0662 0.3345 0.0487
3.000 0.7354 0.01093 0.00250 -0.0657 0.3218 0.0518
3.250 0.7613 0.01099 0.00255 -0.0653 0.3123 0.0563
3.500 0.7871 0.01107 0.00262 -0.0649 0.3039 0.0630
3.750 0.8127 0.01115 0.00273 -0.0644 0.2944 0.0808
4.000 0.8292 0.01004 0.00296 -0.0626 0.2870 0.7205
4.500 0.9121 0.01004 0.00333 -0.0686 0.2592 1.0000
4.750 0.9355 0.01028 0.00349 -0.0677 0.2456 1.0000
5.000 0.9587 0.01055 0.00367 -0.0668 0.2314 1.0000
5.250 0.9821 0.01080 0.00386 -0.0660 0.2192 1.0000
5.500 1.0057 0.01105 0.00406 -0.0652 0.2081 1.0000
5.750 1.0291 0.01132 0.00428 -0.0643 0.1986 1.0000
6.250 1.0759 0.01186 0.00475 -0.0628 0.1815 1.0000
6.500 1.0987 0.01219 0.00502 -0.0619 0.1715 1.0000
6.750 1.1219 0.01247 0.00530 -0.0611 0.1640 1.0000
7.000 1.1449 0.01277 0.00558 -0.0603 0.1570 1.0000
7.250 1.1673 0.01313 0.00590 -0.0594 0.1464 1.0000
7.500 1.1887 0.01356 0.00625 -0.0584 0.1299 1.0000
7.750 1.2015 0.01476 0.00709 -0.0562 0.0694 1.0000
8.000 1.2215 0.01531 0.00761 -0.0550 0.0607 1.0000
8.250 1.2425 0.01574 0.00806 -0.0540 0.0574 1.0000
8.500 1.2630 0.01619 0.00855 -0.0529 0.0545 1.0000
8.750 1.2833 0.01666 0.00906 -0.0517 0.0518 1.0000
9.000 1.3039 0.01706 0.00951 -0.0506 0.0501 1.0000
9.250 1.3247 0.01743 0.00994 -0.0496 0.0485 1.0000
9.500 1.3447 0.01784 0.01041 -0.0485 0.0464 1.0000
9.750 1.3632 0.01834 0.01095 -0.0471 0.0441 1.0000
10.000 1.3800 0.01894 0.01157 -0.0456 0.0410 1.0000
10.250 1.3993 0.01931 0.01200 -0.0444 0.0380 1.0000
10.500 1.4154 0.01985 0.01254 -0.0427 0.0328 1.0000
10.750 1.4242 0.02069 0.01326 -0.0400 0.0198 1.0000
11.000 1.4327 0.02151 0.01410 -0.0372 0.0167 1.0000
11.250 1.4406 0.02239 0.01503 -0.0345 0.0149 1.0000
11.500 1.4487 0.02328 0.01599 -0.0320 0.0139 1.0000
11.750 1.4575 0.02417 0.01696 -0.0298 0.0132 1.0000
12.000 1.4648 0.02518 0.01807 -0.0276 0.0126 1.0000
12.250 1.4707 0.02634 0.01931 -0.0254 0.0120 1.0000
12.500 1.4741 0.02777 0.02084 -0.0234 0.0115 1.0000
12.750 1.4746 0.02953 0.02270 -0.0215 0.0109 1.0000
13.000 1.4753 0.03143 0.02470 -0.0200 0.0106 1.0000
13.250 1.4782 0.03328 0.02666 -0.0189 0.0103 1.0000
13.500 1.4795 0.03542 0.02890 -0.0180 0.0100 1.0000
13.750 1.4784 0.03794 0.03154 -0.0174 0.0097 1.0000
14.000 1.4755 0.04086 0.03458 -0.0172 0.0095 1.0000
14.250 1.4718 0.04406 0.03789 -0.0174 0.0093 1.0000
14.500 1.4648 0.04790 0.04187 -0.0179 0.0091 1.0000
14.750 1.4581 0.05189 0.04599 -0.0189 0.0090 1.0000
15.000 1.4490 0.05642 0.05065 -0.0201 0.0089 1.0000
15.250 1.4386 0.06123 0.05559 -0.0216 0.0088 1.0000
15.500 1.4272 0.06632 0.06080 -0.0233 0.0087 1.0000
15.750 1.4135 0.07187 0.06647 -0.0252 0.0086 1.0000
16.000 1.4008 0.07734 0.07206 -0.0271 0.0085 1.0000
16.250 1.3874 0.08304 0.07788 -0.0293 0.0085 1.0000
16.500 1.3738 0.08888 0.08383 -0.0315 0.0084 1.0000
16.750 1.3619 0.09458 0.08963 -0.0338 0.0083 1.0000
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Polar data table (+)
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