GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Reynolds number: 100,000 Max Cl/Cd: 48.01 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe235-il-100000-n5.txt Download as CSV file: xf-goe235-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 235 (SCHTTE-LANZ) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4252 0.09986 0.09465 -0.0035 1.0000 0.0507
-7.750 -0.4204 0.09699 0.09183 -0.0062 1.0000 0.0517
-7.500 -0.4152 0.09416 0.08904 -0.0117 1.0000 0.0525
-7.250 -0.4033 0.09079 0.08566 -0.0203 1.0000 0.0528
-7.000 -0.3901 0.08688 0.08175 -0.0247 1.0000 0.0531
-6.750 -0.3812 0.08317 0.07810 -0.0215 1.0000 0.0537
-6.500 -0.3698 0.08003 0.07500 -0.0211 1.0000 0.0549
-6.250 -0.3563 0.07695 0.07193 -0.0230 1.0000 0.0565
-6.000 -0.3405 0.07372 0.06870 -0.0266 1.0000 0.0586
-5.750 -0.3111 0.07031 0.06508 -0.0375 1.0000 0.0612
-5.500 -0.2932 0.06661 0.06131 -0.0406 1.0000 0.0618
-5.250 -0.2847 0.06332 0.05814 -0.0389 1.0000 0.0624
-5.000 -0.2745 0.06067 0.05555 -0.0380 1.0000 0.0634
-4.750 -0.2632 0.05827 0.05316 -0.0378 1.0000 0.0646
-4.500 -0.2483 0.05583 0.05070 -0.0386 0.9989 0.0664
-4.250 -0.1937 0.05208 0.04642 -0.0490 0.9901 0.0724
-4.000 -0.1689 0.04841 0.04291 -0.0508 0.9838 0.0746
-3.750 -0.1174 0.04743 0.04130 -0.0576 0.9753 0.0848
-3.500 -0.0928 0.04255 0.03664 -0.0597 0.9679 0.0867
-3.250 -0.0614 0.03993 0.03403 -0.0622 0.9604 0.0900
-3.000 -0.0233 0.03775 0.03151 -0.0658 0.9509 0.1012
-2.750 0.0072 0.03535 0.02915 -0.0676 0.9426 0.1054
-2.500 0.0404 0.03343 0.02704 -0.0698 0.9322 0.1190
-2.250 0.0848 0.02969 0.02259 -0.0713 0.9211 0.0691
-2.000 0.1212 0.02755 0.01989 -0.0721 0.9080 0.0608
-1.750 0.1509 0.02566 0.01788 -0.0725 0.8919 0.0587
-1.500 0.1809 0.02405 0.01596 -0.0722 0.8744 0.0562
-1.250 0.2107 0.02270 0.01416 -0.0715 0.8569 0.0540
-0.750 0.2659 0.02098 0.01179 -0.0696 0.8232 0.0530
-0.500 0.2917 0.01995 0.01075 -0.0690 0.8069 0.0544
-0.250 0.3184 0.01929 0.01002 -0.0683 0.7916 0.0563
0.000 0.3455 0.01865 0.00927 -0.0677 0.7767 0.0572
0.250 0.3726 0.01803 0.00856 -0.0670 0.7609 0.0575
0.500 0.3994 0.01747 0.00794 -0.0662 0.7436 0.0580
0.750 0.4258 0.01697 0.00739 -0.0654 0.7246 0.0588
1.000 0.4521 0.01654 0.00691 -0.0645 0.7031 0.0600
1.250 0.4777 0.01610 0.00645 -0.0636 0.6793 0.0628
1.500 0.5031 0.01576 0.00607 -0.0626 0.6569 0.0659
1.750 0.5291 0.01554 0.00578 -0.0617 0.6354 0.0680
2.000 0.5554 0.01544 0.00556 -0.0610 0.6126 0.0705
2.250 0.5822 0.01536 0.00539 -0.0604 0.5864 0.0746
2.500 0.6089 0.01534 0.00532 -0.0598 0.5501 0.0828
2.750 0.6339 0.01548 0.00516 -0.0589 0.4714 0.0928
3.000 0.6543 0.01409 0.00521 -0.0575 0.3922 1.0000
3.250 0.6784 0.01479 0.00540 -0.0568 0.3256 1.0000
3.500 0.7031 0.01542 0.00563 -0.0563 0.2842 1.0000
3.750 0.7283 0.01595 0.00591 -0.0559 0.2625 1.0000
4.000 0.7538 0.01643 0.00624 -0.0554 0.2489 1.0000
4.250 0.7793 0.01687 0.00660 -0.0550 0.2373 1.0000
4.500 0.8046 0.01733 0.00696 -0.0546 0.2238 1.0000
4.750 0.8300 0.01778 0.00735 -0.0542 0.2133 1.0000
5.000 0.8553 0.01822 0.00776 -0.0538 0.2031 1.0000
5.250 0.8810 0.01860 0.00816 -0.0534 0.1905 1.0000
5.500 0.9064 0.01900 0.00854 -0.0530 0.1731 1.0000
5.750 0.9318 0.01941 0.00893 -0.0526 0.1519 1.0000
6.000 0.9537 0.02042 0.00942 -0.0520 0.0764 1.0000
6.250 0.9759 0.02146 0.01035 -0.0513 0.0647 1.0000
6.500 0.9987 0.02236 0.01126 -0.0506 0.0596 1.0000
6.750 1.0215 0.02323 0.01219 -0.0499 0.0570 1.0000
7.000 1.0443 0.02404 0.01310 -0.0492 0.0551 1.0000
7.250 1.0664 0.02492 0.01408 -0.0484 0.0535 1.0000
7.500 1.0876 0.02588 0.01515 -0.0476 0.0522 1.0000
7.750 1.1077 0.02693 0.01628 -0.0467 0.0510 1.0000
8.000 1.1259 0.02817 0.01757 -0.0457 0.0497 1.0000
8.250 1.1449 0.02927 0.01877 -0.0446 0.0486 1.0000
8.500 1.1636 0.03039 0.02002 -0.0435 0.0474 1.0000
8.750 1.1815 0.03161 0.02133 -0.0424 0.0465 1.0000
9.000 1.1990 0.03291 0.02271 -0.0412 0.0458 1.0000
9.250 1.2166 0.03428 0.02414 -0.0401 0.0452 1.0000
9.500 1.2343 0.03571 0.02566 -0.0389 0.0446 1.0000
9.750 1.2521 0.03723 0.02723 -0.0379 0.0438 1.0000
10.000 1.2700 0.03889 0.02889 -0.0370 0.0429 1.0000
10.250 1.2896 0.04097 0.03090 -0.0363 0.0419 1.0000
10.500 1.3050 0.04262 0.03283 -0.0351 0.0413 1.0000
10.750 1.3203 0.04453 0.03498 -0.0339 0.0408 1.0000
11.000 1.3338 0.04661 0.03731 -0.0326 0.0404 1.0000
11.250 1.3445 0.04884 0.03981 -0.0312 0.0399 1.0000
11.500 1.3518 0.05117 0.04241 -0.0296 0.0393 1.0000
11.750 1.3559 0.05358 0.04507 -0.0279 0.0387 1.0000
12.000 1.3558 0.05598 0.04771 -0.0259 0.0381 1.0000
12.250 1.3537 0.05855 0.05049 -0.0240 0.0376 1.0000
12.500 1.3500 0.06135 0.05349 -0.0226 0.0371 1.0000
12.750 1.3436 0.06452 0.05687 -0.0215 0.0368 1.0000
13.000 1.3338 0.06813 0.06072 -0.0210 0.0367 1.0000
13.250 1.3209 0.07224 0.06506 -0.0212 0.0366 1.0000
13.500 1.3048 0.07697 0.07004 -0.0221 0.0365 1.0000
13.750 1.2840 0.08263 0.07597 -0.0243 0.0365 1.0000
14.000 1.2574 0.08969 0.08331 -0.0280 0.0366 1.0000
14.250 1.2226 0.09904 0.09297 -0.0342 0.0369 1.0000
14.500 1.1713 0.11369 0.10795 -0.0452 0.0375 1.0000
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Polar data table (+)
Polar graphs
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