GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Reynolds number: 200,000 Max Cl/Cd: 74.36 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe187-il-200000.txt Download as CSV file: xf-goe187-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3791 0.11275 0.10933 -0.0128 1.0000 0.0186
-8.750 -0.3751 0.11038 0.10701 -0.0160 1.0000 0.0187
-8.500 -0.3711 0.10776 0.10443 -0.0189 1.0000 0.0188
-8.250 -0.3669 0.10491 0.10162 -0.0217 1.0000 0.0189
-8.000 -0.3609 0.09822 0.09497 -0.0192 1.0000 0.0194
-7.750 -0.3532 0.09418 0.09095 -0.0182 1.0000 0.0198
-7.500 -0.3482 0.09093 0.08774 -0.0188 1.0000 0.0201
-7.250 -0.3423 0.08772 0.08457 -0.0202 1.0000 0.0205
-7.000 -0.3349 0.08446 0.08134 -0.0223 1.0000 0.0209
-6.750 -0.3269 0.08119 0.07809 -0.0246 1.0000 0.0213
-6.500 -0.3186 0.07797 0.07490 -0.0268 1.0000 0.0217
-6.250 -0.3108 0.07485 0.07182 -0.0287 1.0000 0.0222
-6.000 -0.3037 0.07189 0.06888 -0.0302 1.0000 0.0226
-5.750 -0.2998 0.06929 0.06632 -0.0307 1.0000 0.0231
-5.500 -0.3043 0.06750 0.06458 -0.0292 1.0000 0.0234
-5.250 -0.2608 0.06230 0.05926 -0.0385 0.9942 0.0247
-5.000 -0.2035 0.05766 0.05437 -0.0494 0.9864 0.0265
-4.750 -0.1482 0.05429 0.05061 -0.0576 0.9779 0.0272
-4.500 -0.1084 0.04813 0.04424 -0.0638 0.9713 0.0277
-4.250 -0.0818 0.04278 0.03893 -0.0673 0.9606 0.0290
-4.000 -0.0486 0.03929 0.03532 -0.0706 0.9491 0.0307
-3.750 -0.0132 0.03617 0.03199 -0.0734 0.9366 0.0332
-3.500 0.0280 0.03501 0.03033 -0.0747 0.9225 0.0379
-3.250 0.0550 0.03081 0.02587 -0.0759 0.9076 0.0403
-3.000 0.0785 0.02847 0.02346 -0.0762 0.8915 0.0451
-2.000 0.1851 0.02214 0.01580 -0.0744 0.8319 0.0815
-1.750 0.2096 0.02035 0.01394 -0.0742 0.8180 0.0988
-1.500 0.2354 0.02024 0.01352 -0.0738 0.8041 0.1367
-1.250 0.2594 0.01777 0.01110 -0.0738 0.7909 0.1698
-0.750 0.3270 0.01617 0.00839 -0.0702 0.7668 0.0667
-0.500 0.3558 0.01527 0.00726 -0.0691 0.7546 0.0525
-0.250 0.3830 0.01433 0.00623 -0.0684 0.7419 0.0499
0.000 0.4101 0.01383 0.00561 -0.0677 0.7286 0.0520
0.250 0.4363 0.01296 0.00474 -0.0671 0.7153 0.0547
0.500 0.4630 0.01254 0.00426 -0.0666 0.7011 0.0585
1.000 0.5173 0.01207 0.00360 -0.0658 0.6712 0.0929
1.250 0.5493 0.00994 0.00347 -0.0666 0.6545 1.0000
1.500 0.5760 0.01007 0.00340 -0.0662 0.6361 1.0000
1.750 0.6025 0.01022 0.00336 -0.0658 0.6173 1.0000
2.000 0.6290 0.01038 0.00336 -0.0654 0.5970 1.0000
2.250 0.6555 0.01055 0.00339 -0.0651 0.5768 1.0000
2.500 0.6819 0.01075 0.00343 -0.0647 0.5570 1.0000
2.750 0.7082 0.01093 0.00350 -0.0644 0.5353 1.0000
3.000 0.7342 0.01115 0.00355 -0.0640 0.5153 1.0000
3.250 0.7604 0.01138 0.00366 -0.0638 0.4961 1.0000
3.500 0.7867 0.01164 0.00381 -0.0635 0.4809 1.0000
3.750 0.8131 0.01192 0.00403 -0.0633 0.4684 1.0000
4.000 0.8394 0.01221 0.00424 -0.0631 0.4575 1.0000
4.250 0.8657 0.01252 0.00447 -0.0629 0.4470 1.0000
4.500 0.8921 0.01279 0.00474 -0.0628 0.4362 1.0000
4.750 0.9183 0.01309 0.00501 -0.0626 0.4265 1.0000
5.000 0.9445 0.01343 0.00533 -0.0624 0.4181 1.0000
5.250 0.9708 0.01368 0.00565 -0.0622 0.4085 1.0000
5.500 0.9969 0.01400 0.00598 -0.0620 0.4003 1.0000
5.750 1.0228 0.01430 0.00630 -0.0618 0.3915 1.0000
6.000 1.0486 0.01457 0.00668 -0.0616 0.3821 1.0000
6.250 1.0741 0.01487 0.00702 -0.0613 0.3727 1.0000
6.500 1.0994 0.01514 0.00735 -0.0610 0.3624 1.0000
6.750 1.1246 0.01538 0.00771 -0.0607 0.3510 1.0000
7.000 1.1495 0.01564 0.00811 -0.0603 0.3392 1.0000
7.250 1.1740 0.01589 0.00847 -0.0599 0.3252 1.0000
7.500 1.1972 0.01616 0.00876 -0.0593 0.3050 1.0000
7.750 1.2202 0.01641 0.00909 -0.0586 0.2729 1.0000
8.000 1.2401 0.01703 0.00956 -0.0577 0.2177 1.0000
8.250 1.2563 0.01820 0.01043 -0.0565 0.1739 1.0000
8.500 1.2738 0.01925 0.01139 -0.0553 0.1498 1.0000
8.750 1.2928 0.02011 0.01224 -0.0544 0.1314 1.0000
9.000 1.3118 0.02093 0.01302 -0.0534 0.1087 1.0000
9.250 1.3246 0.02234 0.01423 -0.0518 0.0795 1.0000
9.500 1.3339 0.02407 0.01561 -0.0496 0.0328 1.0000
9.750 1.3423 0.02574 0.01733 -0.0471 0.0262 1.0000
10.000 1.3514 0.02719 0.01899 -0.0447 0.0240 1.0000
10.250 1.3555 0.02880 0.02078 -0.0418 0.0223 1.0000
10.500 1.3527 0.03071 0.02284 -0.0383 0.0209 1.0000
10.750 1.3450 0.03321 0.02552 -0.0351 0.0197 1.0000
11.000 1.3419 0.03565 0.02811 -0.0330 0.0191 1.0000
11.250 1.3404 0.03818 0.03080 -0.0315 0.0188 1.0000
11.500 1.3383 0.04098 0.03375 -0.0303 0.0184 1.0000
11.750 1.3363 0.04392 0.03684 -0.0294 0.0181 1.0000
12.000 1.3347 0.04693 0.04002 -0.0286 0.0178 1.0000
12.250 1.3339 0.04994 0.04316 -0.0277 0.0176 1.0000
12.500 1.3338 0.05292 0.04628 -0.0268 0.0174 1.0000
12.750 1.3346 0.05590 0.04941 -0.0258 0.0173 1.0000
13.000 1.3356 0.05896 0.05264 -0.0248 0.0172 1.0000
13.250 1.3357 0.06224 0.05611 -0.0240 0.0172 1.0000
13.500 1.3334 0.06588 0.05995 -0.0236 0.0170 1.0000
13.750 1.3286 0.06985 0.06412 -0.0238 0.0168 1.0000
14.000 1.3216 0.07416 0.06864 -0.0244 0.0165 1.0000
14.250 1.3130 0.07880 0.07348 -0.0255 0.0163 1.0000
14.500 1.3027 0.08378 0.07867 -0.0268 0.0162 1.0000
14.750 1.2913 0.08916 0.08425 -0.0287 0.0160 1.0000
15.000 1.2784 0.09505 0.09036 -0.0311 0.0160 1.0000
15.250 1.2640 0.10148 0.09699 -0.0340 0.0161 1.0000
15.500 1.2484 0.10845 0.10418 -0.0375 0.0162 1.0000
15.750 1.2320 0.11592 0.11186 -0.0415 0.0164 1.0000
16.000 1.2149 0.12389 0.12001 -0.0461 0.0166 1.0000
16.250 1.1972 0.13232 0.12862 -0.0512 0.0168 1.0000
16.500 1.1785 0.14150 0.13798 -0.0569 0.0171 1.0000
16.750 1.1591 0.15144 0.14807 -0.0632 0.0175 1.0000
17.000 1.1381 0.16249 0.15923 -0.0702 0.0182 1.0000
17.250 1.1163 0.17436 0.17118 -0.0774 0.0191 1.0000
17.500 1.1063 0.18343 0.18030 -0.0825 0.0197 1.0000
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