GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.3 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe344-il-1000000.txt Download as CSV file: xf-goe344-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 344 (PFALZ 71) 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5548 0.13597 0.13417 0.0054 1.0000 0.0142
-11.750 -0.5476 0.13341 0.13162 0.0046 1.0000 0.0146
-11.500 -0.9849 0.03001 0.02722 -0.0482 1.0000 0.0129
-11.250 -0.9721 0.02724 0.02418 -0.0474 1.0000 0.0133
-11.000 -0.9553 0.02547 0.02220 -0.0464 1.0000 0.0135
-10.750 -0.9424 0.02293 0.01934 -0.0452 1.0000 0.0140
-10.500 -0.9230 0.02178 0.01811 -0.0442 1.0000 0.0145
-10.250 -0.9001 0.02139 0.01768 -0.0434 1.0000 0.0149
-10.000 -0.8768 0.02107 0.01733 -0.0426 1.0000 0.0154
-9.750 -0.8540 0.02063 0.01684 -0.0418 1.0000 0.0159
-9.500 -0.8317 0.02006 0.01617 -0.0409 1.0000 0.0165
-9.250 -0.8088 0.01961 0.01562 -0.0400 1.0000 0.0170
-9.000 -0.7850 0.01940 0.01533 -0.0392 1.0000 0.0173
-8.750 -0.7671 0.01764 0.01337 -0.0379 1.0000 0.0182
-8.500 -0.7436 0.01743 0.01315 -0.0371 1.0000 0.0187
-8.250 -0.7201 0.01723 0.01294 -0.0362 1.0000 0.0193
-8.000 -0.6969 0.01691 0.01256 -0.0353 1.0000 0.0199
-7.750 -0.6741 0.01648 0.01205 -0.0343 1.0000 0.0206
-7.500 -0.6509 0.01621 0.01170 -0.0333 1.0000 0.0212
-7.250 -0.6272 0.01617 0.01162 -0.0324 1.0000 0.0216
-7.000 -0.6074 0.01455 0.00978 -0.0312 1.0000 0.0227
-6.750 -0.5846 0.01419 0.00941 -0.0302 1.0000 0.0234
-6.500 -0.5617 0.01391 0.00909 -0.0292 1.0000 0.0241
-6.250 -0.5387 0.01362 0.00876 -0.0282 1.0000 0.0248
-6.000 -0.5078 0.01333 0.00842 -0.0289 0.9993 0.0257
-5.750 -0.4740 0.01300 0.00802 -0.0302 0.9982 0.0265
-5.500 -0.4407 0.01275 0.00770 -0.0313 0.9971 0.0270
-5.250 -0.4101 0.01156 0.00636 -0.0320 0.9963 0.0283
-5.000 -0.3774 0.01106 0.00584 -0.0331 0.9954 0.0294
-4.750 -0.3438 0.01070 0.00545 -0.0344 0.9946 0.0303
-4.500 -0.3099 0.01033 0.00505 -0.0356 0.9933 0.0311
-4.250 -0.2755 0.00999 0.00468 -0.0370 0.9910 0.0322
-4.000 -0.2404 0.00964 0.00430 -0.0385 0.9889 0.0330
-3.750 -0.2052 0.00933 0.00397 -0.0400 0.9871 0.0336
-3.500 -0.1696 0.00900 0.00361 -0.0416 0.9856 0.0343
-3.250 -0.1338 0.00851 0.00307 -0.0432 0.9843 0.0362
-3.000 -0.1017 0.00821 0.00278 -0.0440 0.9805 0.0380
-2.750 -0.0676 0.00794 0.00252 -0.0452 0.9766 0.0396
-2.500 -0.0314 0.00770 0.00227 -0.0469 0.9737 0.0414
-2.250 0.0002 0.00744 0.00202 -0.0476 0.9685 0.0453
-2.000 0.0309 0.00718 0.00183 -0.0480 0.9611 0.0562
-1.750 0.0625 0.00691 0.00168 -0.0487 0.9515 0.0818
-1.500 0.0958 0.00672 0.00156 -0.0497 0.9394 0.1003
-1.250 0.1277 0.00660 0.00146 -0.0504 0.9217 0.1146
-1.000 0.1566 0.00656 0.00138 -0.0503 0.8987 0.1257
-0.750 0.1837 0.00659 0.00133 -0.0499 0.8714 0.1340
-0.500 0.2097 0.00664 0.00128 -0.0492 0.8270 0.1436
-0.250 0.2329 0.00693 0.00123 -0.0479 0.7403 0.1508
0.000 0.2583 0.00712 0.00125 -0.0473 0.6909 0.1606
0.250 0.2848 0.00721 0.00125 -0.0469 0.6546 0.1734
0.500 0.3113 0.00729 0.00125 -0.0465 0.6163 0.1895
0.750 0.3375 0.00730 0.00130 -0.0462 0.5770 0.2491
1.000 0.3638 0.00728 0.00135 -0.0459 0.5428 0.3217
1.250 0.3898 0.00714 0.00141 -0.0456 0.5115 0.4360
1.500 0.4008 0.00589 0.00153 -0.0417 0.4847 0.9574
1.750 0.4305 0.00611 0.00161 -0.0418 0.4456 0.9799
2.000 0.4672 0.00642 0.00171 -0.0438 0.3964 0.9898
2.250 0.5111 0.00678 0.00187 -0.0475 0.3534 0.9953
2.500 0.5578 0.00709 0.00202 -0.0518 0.3220 0.9990
2.750 0.5894 0.00729 0.00211 -0.0527 0.2999 1.0000
3.000 0.6142 0.00743 0.00218 -0.0520 0.2852 1.0000
3.250 0.6389 0.00756 0.00225 -0.0512 0.2727 1.0000
3.500 0.6636 0.00768 0.00233 -0.0505 0.2616 1.0000
3.750 0.6883 0.00780 0.00242 -0.0498 0.2507 1.0000
4.000 0.7128 0.00793 0.00251 -0.0490 0.2398 1.0000
4.250 0.7372 0.00809 0.00262 -0.0482 0.2289 1.0000
4.500 0.7618 0.00822 0.00273 -0.0475 0.2185 1.0000
4.750 0.7862 0.00837 0.00285 -0.0467 0.2074 1.0000
5.000 0.8105 0.00856 0.00298 -0.0459 0.1935 1.0000
5.250 0.8348 0.00876 0.00313 -0.0452 0.1782 1.0000
5.500 0.8588 0.00902 0.00331 -0.0444 0.1596 1.0000
5.750 0.8823 0.00936 0.00353 -0.0435 0.1349 1.0000
6.000 0.9047 0.00988 0.00385 -0.0426 0.0999 1.0000
6.250 0.9278 0.01036 0.00420 -0.0417 0.0762 1.0000
6.500 0.9520 0.01074 0.00451 -0.0410 0.0646 1.0000
6.750 0.9769 0.01102 0.00479 -0.0405 0.0592 1.0000
7.000 1.0015 0.01139 0.00513 -0.0399 0.0527 1.0000
7.250 1.0269 0.01164 0.00541 -0.0394 0.0496 1.0000
7.500 1.0515 0.01200 0.00575 -0.0389 0.0453 1.0000
7.750 1.0765 0.01232 0.00609 -0.0384 0.0420 1.0000
8.000 1.1017 0.01259 0.00638 -0.0380 0.0391 1.0000
8.250 1.1257 0.01305 0.00681 -0.0373 0.0346 1.0000
8.500 1.1510 0.01330 0.00710 -0.0369 0.0324 1.0000
8.750 1.1750 0.01372 0.00750 -0.0364 0.0285 1.0000
9.000 1.1993 0.01410 0.00790 -0.0358 0.0254 1.0000
9.250 1.2220 0.01467 0.00845 -0.0350 0.0215 1.0000
9.500 1.2462 0.01504 0.00886 -0.0345 0.0197 1.0000
9.750 1.2686 0.01562 0.00944 -0.0337 0.0175 1.0000
10.000 1.2910 0.01618 0.01006 -0.0329 0.0163 1.0000
10.250 1.3136 0.01668 0.01061 -0.0321 0.0153 1.0000
10.500 1.3351 0.01728 0.01125 -0.0312 0.0143 1.0000
10.750 1.3531 0.01827 0.01233 -0.0297 0.0131 1.0000
11.000 1.3749 0.01878 0.01290 -0.0289 0.0127 1.0000
11.250 1.3958 0.01935 0.01354 -0.0279 0.0121 1.0000
11.500 1.4158 0.01999 0.01424 -0.0268 0.0115 1.0000
11.750 1.4343 0.02074 0.01506 -0.0256 0.0110 1.0000
12.000 1.4491 0.02179 0.01620 -0.0238 0.0104 1.0000
12.250 1.4593 0.02318 0.01772 -0.0214 0.0100 1.0000
12.500 1.4760 0.02391 0.01854 -0.0199 0.0098 1.0000
12.750 1.4907 0.02475 0.01948 -0.0181 0.0096 1.0000
13.000 1.5029 0.02568 0.02051 -0.0161 0.0093 1.0000
13.250 1.5119 0.02665 0.02159 -0.0135 0.0091 1.0000
13.500 1.5176 0.02771 0.02273 -0.0105 0.0088 1.0000
13.750 1.5224 0.02889 0.02401 -0.0076 0.0086 1.0000
14.000 1.5260 0.03024 0.02546 -0.0050 0.0084 1.0000
14.250 1.5278 0.03183 0.02715 -0.0025 0.0083 1.0000
14.500 1.5268 0.03378 0.02921 -0.0004 0.0081 1.0000
14.750 1.5220 0.03629 0.03184 0.0013 0.0080 1.0000
15.000 1.5131 0.03956 0.03525 0.0023 0.0078 1.0000
15.250 1.4986 0.04413 0.03999 0.0018 0.0077 1.0000
15.500 1.4826 0.04976 0.04580 -0.0004 0.0076 1.0000
15.750 1.4629 0.05664 0.05287 -0.0039 0.0076 1.0000
16.000 1.4431 0.06393 0.06033 -0.0078 0.0075 1.0000
16.250 1.4210 0.07173 0.06830 -0.0119 0.0075 1.0000
16.500 1.3992 0.07953 0.07624 -0.0158 0.0075 1.0000
16.750 1.3782 0.08720 0.08404 -0.0196 0.0075 1.0000
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