GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Reynolds number: 500,000 Max Cl/Cd: 100.87 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe187-il-500000.txt Download as CSV file: xf-goe187-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 187 (SCHTTE-LANZ 2U10) 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2789 0.10227 0.10021 -0.0189 1.0000 0.0092
-9.250 -0.2771 0.09893 0.09688 -0.0203 1.0000 0.0092
-9.000 -0.2759 0.09550 0.09348 -0.0218 1.0000 0.0093
-8.750 -0.2733 0.09198 0.08997 -0.0230 1.0000 0.0093
-8.250 -0.2645 0.08340 0.08143 -0.0224 1.0000 0.0096
-8.000 -0.2610 0.07998 0.07803 -0.0226 1.0000 0.0098
-7.750 -0.2586 0.07664 0.07471 -0.0233 1.0000 0.0099
-7.500 -0.2571 0.07337 0.07147 -0.0239 1.0000 0.0101
-7.250 -0.2569 0.07024 0.06837 -0.0244 1.0000 0.0104
-7.000 -0.2604 0.06744 0.06562 -0.0243 1.0000 0.0105
-6.750 -0.2566 0.06383 0.06204 -0.0268 0.9954 0.0109
-6.000 -0.2769 0.06664 0.06465 -0.0378 0.9923 0.0111
-5.750 -0.2423 0.06171 0.05966 -0.0456 0.9817 0.0117
-5.500 -0.2069 0.05698 0.05483 -0.0527 0.9657 0.0122
-5.250 -0.1663 0.05255 0.05023 -0.0595 0.9446 0.0128
-5.000 -0.1325 0.04891 0.04637 -0.0632 0.9188 0.0131
-4.750 -0.1068 0.04579 0.04301 -0.0645 0.8938 0.0131
-4.500 -0.0824 0.04281 0.03980 -0.0652 0.8706 0.0132
-4.250 -0.0576 0.03991 0.03665 -0.0658 0.8487 0.0132
-4.000 -0.0395 0.03493 0.03145 -0.0669 0.8296 0.0137
-3.750 -0.0174 0.03250 0.02886 -0.0674 0.8106 0.0142
-3.500 0.0074 0.03027 0.02642 -0.0677 0.7932 0.0148
-3.250 0.0340 0.02810 0.02401 -0.0678 0.7776 0.0157
-3.000 0.0626 0.02609 0.02172 -0.0677 0.7637 0.0172
-2.750 0.0957 0.02587 0.02110 -0.0665 0.7511 0.0188
-2.500 0.1214 0.02158 0.01642 -0.0668 0.7408 0.0198
-2.000 0.1747 0.01894 0.01346 -0.0670 0.7188 0.0242
-1.750 0.2051 0.01934 0.01359 -0.0662 0.7081 0.0270
-1.500 0.2338 0.01857 0.01254 -0.0658 0.6979 0.0273
-1.250 0.2607 0.01517 0.00888 -0.0660 0.6884 0.0298
-1.000 0.2888 0.01420 0.00780 -0.0659 0.6784 0.0321
-0.750 0.3174 0.01357 0.00699 -0.0656 0.6686 0.0358
-0.500 0.3461 0.01244 0.00568 -0.0652 0.6587 0.0342
-0.250 0.3751 0.01145 0.00450 -0.0646 0.6482 0.0289
0.000 0.4034 0.01126 0.00422 -0.0643 0.6367 0.0275
0.250 0.4307 0.01034 0.00325 -0.0640 0.6248 0.0280
0.500 0.4581 0.00979 0.00266 -0.0639 0.6112 0.0315
0.750 0.4858 0.00959 0.00239 -0.0638 0.5941 0.0358
1.000 0.5135 0.00946 0.00214 -0.0636 0.5737 0.0393
1.250 0.5411 0.00934 0.00189 -0.0635 0.5489 0.0501
2.000 0.6240 0.00763 0.00192 -0.0641 0.4641 1.0000
2.250 0.6509 0.00785 0.00199 -0.0640 0.4456 1.0000
2.500 0.6779 0.00806 0.00208 -0.0639 0.4304 1.0000
2.750 0.7049 0.00827 0.00219 -0.0638 0.4176 1.0000
3.000 0.7321 0.00845 0.00230 -0.0638 0.4061 1.0000
3.250 0.7593 0.00862 0.00241 -0.0637 0.3962 1.0000
3.500 0.7864 0.00882 0.00255 -0.0637 0.3881 1.0000
3.750 0.8136 0.00897 0.00269 -0.0636 0.3802 1.0000
4.000 0.8407 0.00916 0.00284 -0.0636 0.3728 1.0000
4.250 0.8678 0.00932 0.00298 -0.0635 0.3649 1.0000
4.500 0.8948 0.00950 0.00314 -0.0635 0.3583 1.0000
4.750 0.9219 0.00967 0.00333 -0.0635 0.3506 1.0000
5.000 0.9488 0.00984 0.00350 -0.0634 0.3429 1.0000
5.250 0.9755 0.01003 0.00368 -0.0634 0.3345 1.0000
5.500 1.0025 0.01019 0.00386 -0.0633 0.3264 1.0000
5.750 1.0290 0.01041 0.00409 -0.0632 0.3186 1.0000
6.000 1.0559 0.01056 0.00429 -0.0632 0.3096 1.0000
6.250 1.0824 0.01076 0.00451 -0.0631 0.2999 1.0000
6.500 1.1086 0.01099 0.00473 -0.0630 0.2845 1.0000
6.750 1.1340 0.01131 0.00499 -0.0628 0.2571 1.0000
7.000 1.1564 0.01201 0.00541 -0.0623 0.1994 1.0000
7.250 1.1769 0.01298 0.00610 -0.0616 0.1553 1.0000
7.500 1.1988 0.01372 0.00669 -0.0610 0.1223 1.0000
7.750 1.2212 0.01438 0.00724 -0.0604 0.1025 1.0000
8.000 1.2436 0.01500 0.00783 -0.0599 0.0910 1.0000
8.250 1.2653 0.01568 0.00847 -0.0592 0.0790 1.0000
8.500 1.2844 0.01663 0.00916 -0.0583 0.0358 1.0000
8.750 1.2995 0.01803 0.01048 -0.0566 0.0163 1.0000
9.000 1.3172 0.01909 0.01171 -0.0551 0.0131 1.0000
9.250 1.3364 0.01987 0.01263 -0.0541 0.0121 1.0000
9.500 1.3531 0.02086 0.01375 -0.0526 0.0112 1.0000
9.750 1.3674 0.02200 0.01502 -0.0509 0.0104 1.0000
10.000 1.3782 0.02333 0.01647 -0.0488 0.0098 1.0000
10.250 1.3833 0.02495 0.01823 -0.0459 0.0093 1.0000
10.500 1.3796 0.02679 0.02021 -0.0418 0.0090 1.0000
10.750 1.3710 0.02913 0.02270 -0.0379 0.0087 1.0000
11.250 1.3684 0.03360 0.02744 -0.0335 0.0083 1.0000
11.500 1.3750 0.03536 0.02934 -0.0326 0.0080 1.0000
11.750 1.3779 0.03762 0.03172 -0.0317 0.0077 1.0000
12.000 1.3782 0.04028 0.03451 -0.0309 0.0074 1.0000
12.250 1.3775 0.04317 0.03752 -0.0303 0.0073 1.0000
12.500 1.3763 0.04618 0.04067 -0.0298 0.0071 1.0000
12.750 1.3747 0.04932 0.04393 -0.0294 0.0070 1.0000
13.000 1.3724 0.05258 0.04732 -0.0291 0.0069 1.0000
13.250 1.3697 0.05596 0.05083 -0.0290 0.0068 1.0000
13.500 1.3662 0.05949 0.05450 -0.0289 0.0067 1.0000
13.750 1.3618 0.06320 0.05835 -0.0290 0.0066 1.0000
14.000 1.3565 0.06713 0.06241 -0.0293 0.0065 1.0000
14.250 1.3499 0.07130 0.06673 -0.0298 0.0065 1.0000
14.500 1.3421 0.07583 0.07142 -0.0306 0.0065 1.0000
14.750 1.3331 0.08072 0.07647 -0.0318 0.0064 1.0000
15.000 1.3221 0.08610 0.08204 -0.0334 0.0065 1.0000
15.250 1.3093 0.09206 0.08819 -0.0355 0.0065 1.0000
15.500 1.2944 0.09865 0.09499 -0.0381 0.0067 1.0000
15.750 1.2789 0.10556 0.10209 -0.0412 0.0068 1.0000
16.000 1.2628 0.11285 0.10956 -0.0447 0.0069 1.0000
16.250 1.2468 0.12041 0.11729 -0.0486 0.0070 1.0000
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Polar data table (+)
Polar graphs
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