GOE 507 AIRFOIL (goe507-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 507 AIRFOIL (goe507-il) Reynolds number: 500,000 Max Cl/Cd: 95.13 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe507-il-500000.txt Download as CSV file: xf-goe507-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 507 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.8237 0.03587 0.03301 -0.0671 1.0000 0.0211
-10.750 -0.8405 0.03040 0.02701 -0.0652 1.0000 0.0215
-10.500 -0.8397 0.02765 0.02391 -0.0627 1.0000 0.0221
-10.250 -0.8399 0.02517 0.02113 -0.0596 1.0000 0.0227
-10.000 -0.8270 0.02477 0.02073 -0.0573 1.0000 0.0234
-9.750 -0.8098 0.02510 0.02113 -0.0553 1.0000 0.0241
-9.500 -0.7933 0.02487 0.02087 -0.0536 0.9997 0.0249
-9.250 -0.7636 0.02304 0.01871 -0.0554 0.9970 0.0262
-9.000 -0.7342 0.02102 0.01633 -0.0571 0.9943 0.0277
-8.750 -0.7001 0.02137 0.01677 -0.0585 0.9918 0.0287
-8.500 -0.6655 0.02176 0.01719 -0.0599 0.9891 0.0300
-8.250 -0.6329 0.02093 0.01615 -0.0614 0.9864 0.0319
-8.000 -0.6005 0.01978 0.01479 -0.0631 0.9842 0.0337
-7.750 -0.5663 0.01994 0.01499 -0.0646 0.9818 0.0348
-7.500 -0.5347 0.01991 0.01494 -0.0655 0.9781 0.0364
-7.250 -0.5014 0.01958 0.01443 -0.0668 0.9753 0.0387
-7.000 -0.4694 0.01828 0.01294 -0.0683 0.9731 0.0408
-6.750 -0.4340 0.01800 0.01267 -0.0702 0.9716 0.0423
-6.500 -0.3984 0.01781 0.01246 -0.0720 0.9700 0.0445
-6.250 -0.3704 0.01751 0.01203 -0.0720 0.9645 0.0466
-6.000 -0.3373 0.01764 0.01203 -0.0730 0.9611 0.0480
-5.750 -0.3084 0.01549 0.00975 -0.0740 0.9579 0.0508
-5.500 -0.2781 0.01503 0.00925 -0.0746 0.9538 0.0527
-5.250 -0.2506 0.01457 0.00873 -0.0745 0.9472 0.0545
-5.000 -0.2208 0.01414 0.00820 -0.0748 0.9422 0.0564
-4.750 -0.1945 0.01376 0.00773 -0.0743 0.9350 0.0576
-4.500 -0.1670 0.01366 0.00754 -0.0739 0.9285 0.0586
-4.250 -0.1422 0.01231 0.00609 -0.0734 0.9221 0.0605
-4.000 -0.1171 0.01168 0.00543 -0.0727 0.9148 0.0618
-3.750 -0.0908 0.01126 0.00498 -0.0722 0.9086 0.0634
-3.500 -0.0655 0.01093 0.00463 -0.0716 0.9013 0.0649
-3.250 -0.0391 0.01060 0.00425 -0.0711 0.8958 0.0660
-3.000 -0.0133 0.01030 0.00393 -0.0705 0.8894 0.0673
-2.750 0.0128 0.01003 0.00362 -0.0700 0.8832 0.0685
-2.500 0.0395 0.00982 0.00337 -0.0695 0.8776 0.0698
-2.250 0.0656 0.00963 0.00317 -0.0690 0.8708 0.0709
-2.000 0.0919 0.00937 0.00287 -0.0685 0.8649 0.0721
-1.750 0.1177 0.00910 0.00260 -0.0679 0.8584 0.0743
-1.500 0.1441 0.00891 0.00239 -0.0674 0.8517 0.0769
-1.250 0.1708 0.00876 0.00223 -0.0670 0.8456 0.0800
-1.000 0.1973 0.00863 0.00210 -0.0665 0.8382 0.0837
-0.750 0.2242 0.00847 0.00196 -0.0661 0.8319 0.0948
-0.500 0.2491 0.00812 0.00195 -0.0655 0.8237 0.1794
-0.250 0.2757 0.00798 0.00190 -0.0650 0.8164 0.2193
0.000 0.3013 0.00781 0.00184 -0.0644 0.8055 0.2523
0.250 0.3261 0.00754 0.00179 -0.0637 0.7939 0.3228
0.500 0.3473 0.00689 0.00176 -0.0624 0.7835 0.5383
0.750 0.3832 0.00585 0.00190 -0.0635 0.7718 0.9445
1.000 0.4422 0.00591 0.00191 -0.0699 0.7566 0.9848
1.250 0.5013 0.00595 0.00187 -0.0766 0.7407 0.9999
1.500 0.5250 0.00600 0.00185 -0.0755 0.7222 1.0000
1.750 0.5483 0.00606 0.00184 -0.0744 0.7019 1.0000
2.000 0.5711 0.00616 0.00185 -0.0732 0.6778 1.0000
2.250 0.5935 0.00629 0.00186 -0.0719 0.6483 1.0000
2.500 0.6155 0.00647 0.00190 -0.0705 0.6133 1.0000
2.750 0.6365 0.00672 0.00197 -0.0690 0.5746 1.0000
3.000 0.6576 0.00701 0.00209 -0.0675 0.5402 1.0000
3.250 0.6793 0.00728 0.00223 -0.0662 0.5119 1.0000
3.500 0.7013 0.00754 0.00237 -0.0650 0.4829 1.0000
3.750 0.7231 0.00782 0.00254 -0.0637 0.4516 1.0000
4.000 0.7447 0.00812 0.00270 -0.0624 0.4161 1.0000
4.250 0.7654 0.00849 0.00289 -0.0610 0.3741 1.0000
4.500 0.7850 0.00897 0.00313 -0.0595 0.3208 1.0000
5.000 0.8191 0.01044 0.00386 -0.0557 0.1801 1.0000
5.250 0.8329 0.01153 0.00443 -0.0534 0.0904 1.0000
5.500 0.8540 0.01199 0.00483 -0.0521 0.0788 1.0000
5.750 0.8748 0.01248 0.00529 -0.0508 0.0716 1.0000
6.000 0.8973 0.01281 0.00566 -0.0497 0.0681 1.0000
6.250 0.9190 0.01321 0.00608 -0.0486 0.0641 1.0000
6.500 0.9377 0.01389 0.00675 -0.0470 0.0590 1.0000
6.750 0.9603 0.01420 0.00712 -0.0460 0.0564 1.0000
7.000 0.9821 0.01458 0.00752 -0.0449 0.0529 1.0000
7.250 1.0005 0.01524 0.00818 -0.0434 0.0488 1.0000
7.500 1.0215 0.01568 0.00867 -0.0422 0.0458 1.0000
7.750 1.0433 0.01604 0.00906 -0.0411 0.0427 1.0000
8.000 1.0621 0.01664 0.00963 -0.0397 0.0394 1.0000
8.250 1.0818 0.01715 0.01020 -0.0383 0.0370 1.0000
8.500 1.1032 0.01749 0.01058 -0.0373 0.0345 1.0000
8.750 1.1221 0.01801 0.01109 -0.0359 0.0325 1.0000
9.000 1.1365 0.01889 0.01202 -0.0338 0.0307 1.0000
9.250 1.1553 0.01939 0.01259 -0.0323 0.0291 1.0000
9.500 1.1740 0.01984 0.01306 -0.0310 0.0274 1.0000
9.750 1.1880 0.02054 0.01376 -0.0289 0.0260 1.0000
10.000 1.1956 0.02167 0.01496 -0.0258 0.0249 1.0000
10.250 1.2097 0.02232 0.01570 -0.0237 0.0240 1.0000
10.500 1.2222 0.02312 0.01657 -0.0215 0.0232 1.0000
10.750 1.2348 0.02388 0.01739 -0.0194 0.0223 1.0000
11.000 1.2466 0.02468 0.01822 -0.0174 0.0214 1.0000
11.250 1.2541 0.02599 0.01959 -0.0151 0.0207 1.0000
11.500 1.2619 0.02744 0.02114 -0.0128 0.0200 1.0000
11.750 1.2725 0.02851 0.02233 -0.0110 0.0195 1.0000
12.000 1.2823 0.02965 0.02358 -0.0092 0.0188 1.0000
12.250 1.2909 0.03094 0.02498 -0.0074 0.0183 1.0000
12.500 1.2988 0.03222 0.02635 -0.0058 0.0177 1.0000
12.750 1.3059 0.03366 0.02788 -0.0042 0.0174 1.0000
13.000 1.3116 0.03526 0.02955 -0.0027 0.0170 1.0000
13.250 1.3156 0.03716 0.03154 -0.0012 0.0167 1.0000
13.500 1.3126 0.04033 0.03487 0.0005 0.0162 1.0000
13.750 1.3132 0.04250 0.03722 0.0017 0.0160 1.0000
14.000 1.3123 0.04501 0.03991 0.0028 0.0158 1.0000
14.250 1.3095 0.04780 0.04288 0.0035 0.0156 1.0000
14.500 1.3069 0.05057 0.04582 0.0038 0.0153 1.0000
14.750 1.3036 0.05353 0.04893 0.0038 0.0149 1.0000
15.000 1.2952 0.05744 0.05302 0.0035 0.0148 1.0000
15.250 1.2867 0.06149 0.05724 0.0027 0.0146 1.0000
15.500 1.2730 0.06659 0.06255 0.0012 0.0146 1.0000
15.750 1.2674 0.07068 0.06675 -0.0004 0.0143 1.0000
16.000 1.2506 0.07690 0.07317 -0.0031 0.0143 1.0000
16.250 1.2326 0.08372 0.08019 -0.0065 0.0142 1.0000
16.500 1.2188 0.09012 0.08673 -0.0100 0.0141 1.0000
16.750 1.1946 0.09891 0.09573 -0.0150 0.0141 1.0000
17.000 1.1515 0.11258 0.10969 -0.0234 0.0144 1.0000
17.250 1.0071 0.15599 0.15360 -0.0501 0.0160 1.0000
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