GOE 513 AIRFOIL (goe513-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 513 AIRFOIL (goe513-il) Reynolds number: 100,000 Max Cl/Cd: 44.5 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe513-il-100000.txt Download as CSV file: xf-goe513-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 513 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2831 0.09759 0.09343 -0.0396 0.9649 0.1766
-7.250 -0.3261 0.09526 0.09110 -0.0439 0.9527 0.1842
-7.000 -0.3447 0.09130 0.08712 -0.0448 0.9404 0.1866
-6.750 -0.3078 0.08733 0.08316 -0.0459 0.9350 0.1890
-6.500 -0.4781 0.05724 0.05152 -0.0429 0.9156 0.1018
-6.250 -0.4554 0.05362 0.04774 -0.0433 0.9079 0.0990
-6.000 -0.4513 0.04973 0.04351 -0.0405 0.8970 0.0963
-5.750 -0.4380 0.04472 0.03773 -0.0389 0.8901 0.0937
-5.500 -0.4281 0.04228 0.03485 -0.0358 0.8779 0.0937
-5.250 -0.3910 0.03960 0.03166 -0.0372 0.8727 0.0940
-5.000 -0.3739 0.03787 0.02959 -0.0349 0.8596 0.0941
-4.750 -0.3461 0.03624 0.02765 -0.0344 0.8489 0.0946
-4.500 -0.3039 0.03448 0.02563 -0.0362 0.8418 0.0959
-4.250 -0.2744 0.03330 0.02426 -0.0359 0.8301 0.0976
-4.000 -0.2259 0.03181 0.02250 -0.0387 0.8243 0.1013
-3.750 -0.1948 0.03056 0.02137 -0.0389 0.8123 0.1046
-3.500 -0.1440 0.02903 0.01982 -0.0422 0.8072 0.1098
-3.250 -0.1132 0.02803 0.01881 -0.0420 0.7957 0.1150
-3.000 -0.0656 0.02653 0.01739 -0.0446 0.7906 0.1274
-2.750 -0.0100 0.02483 0.01614 -0.0486 0.7879 0.1690
-2.500 0.0035 0.02498 0.01644 -0.0447 0.7735 0.2405
-2.250 0.0254 0.02516 0.01651 -0.0423 0.7634 0.2810
-2.000 0.0626 0.02484 0.01603 -0.0430 0.7550 0.3086
-1.750 0.1273 0.02395 0.01510 -0.0493 0.7511 0.3380
-1.500 0.1485 0.02376 0.01488 -0.0476 0.7366 0.3559
-1.250 0.1846 0.02332 0.01439 -0.0488 0.7257 0.3792
-1.000 0.2347 0.02261 0.01356 -0.0527 0.7160 0.4012
-0.750 0.2664 0.02225 0.01320 -0.0533 0.7028 0.4109
-0.500 0.3212 0.02170 0.01244 -0.0582 0.6926 0.4206
-0.250 0.3606 0.02133 0.01209 -0.0604 0.6793 0.4285
0.000 0.3943 0.02117 0.01189 -0.0615 0.6662 0.4387
0.250 0.4511 0.02070 0.01140 -0.0671 0.6532 0.4529
0.500 0.4991 0.02030 0.01099 -0.0710 0.6406 0.4691
0.750 0.5202 0.02019 0.01098 -0.0696 0.6282 0.4876
1.000 0.7259 0.02037 0.01219 -0.1031 0.6059 0.9512
1.250 0.8768 0.02048 0.01180 -0.1274 0.5857 1.0000
1.500 0.8925 0.02078 0.01202 -0.1251 0.5745 1.0000
1.750 0.9152 0.02105 0.01210 -0.1242 0.5648 1.0000
2.000 0.9345 0.02134 0.01227 -0.1226 0.5541 1.0000
2.250 0.9534 0.02170 0.01252 -0.1210 0.5440 1.0000
2.500 0.9758 0.02203 0.01267 -0.1200 0.5339 1.0000
2.750 0.9906 0.02246 0.01306 -0.1176 0.5237 1.0000
3.000 1.0150 0.02281 0.01322 -0.1171 0.5139 1.0000
3.250 1.0259 0.02329 0.01373 -0.1140 0.5041 1.0000
3.500 1.0500 0.02367 0.01393 -0.1134 0.4948 1.0000
3.750 1.0591 0.02417 0.01449 -0.1100 0.4852 1.0000
4.000 1.0811 0.02454 0.01471 -0.1090 0.4761 1.0000
4.250 1.0900 0.02505 0.01527 -0.1056 0.4668 1.0000
4.500 1.1092 0.02539 0.01549 -0.1040 0.4578 1.0000
4.750 1.1191 0.02589 0.01603 -0.1008 0.4489 1.0000
5.000 1.1346 0.02624 0.01632 -0.0985 0.4404 1.0000
5.250 1.1491 0.02672 0.01677 -0.0962 0.4325 1.0000
5.500 1.1586 0.02718 0.01725 -0.0929 0.4244 1.0000
5.750 1.1852 0.02752 0.01741 -0.0928 0.4177 1.0000
6.000 1.1844 0.02819 0.01824 -0.0877 0.4100 1.0000
6.250 1.2035 0.02852 0.01849 -0.0862 0.4034 1.0000
6.500 1.2169 0.02910 0.01905 -0.0837 0.3970 1.0000
6.750 1.2222 0.02970 0.01974 -0.0798 0.3904 1.0000
7.000 1.2460 0.03000 0.01992 -0.0792 0.3847 1.0000
7.250 1.2558 0.03074 0.02071 -0.0762 0.3795 1.0000
7.500 1.2591 0.03154 0.02161 -0.0721 0.3741 1.0000
7.750 1.2768 0.03203 0.02208 -0.0705 0.3693 1.0000
8.000 1.3089 0.03251 0.02240 -0.0715 0.3649 1.0000
8.250 1.2983 0.03362 0.02375 -0.0651 0.3604 1.0000
8.500 1.3017 0.03445 0.02466 -0.0611 0.3559 1.0000
8.750 1.3210 0.03495 0.02514 -0.0599 0.3517 1.0000
9.000 1.3566 0.03548 0.02553 -0.0617 0.3478 1.0000
9.250 1.3386 0.03686 0.02716 -0.0542 0.3445 1.0000
9.500 1.3266 0.03805 0.02851 -0.0480 0.3412 1.0000
9.750 1.3258 0.03906 0.02960 -0.0436 0.3380 1.0000
10.000 1.3438 0.03972 0.03026 -0.0424 0.3346 1.0000
10.250 1.3925 0.04028 0.03069 -0.0464 0.3309 1.0000
10.500 1.3505 0.04204 0.03270 -0.0357 0.3286 1.0000
10.750 1.3134 0.04433 0.03523 -0.0270 0.3259 1.0000
11.000 1.2816 0.04702 0.03811 -0.0201 0.3232 1.0000
11.250 1.2636 0.04947 0.04069 -0.0154 0.3204 1.0000
11.500 1.2674 0.05107 0.04235 -0.0132 0.3179 1.0000
11.750 1.3270 0.05021 0.04138 -0.0166 0.3152 1.0000
12.000 0.6121 0.14373 0.13593 -0.0215 0.3508 1.0000
12.250 0.6389 0.14651 0.13873 -0.0214 0.3492 1.0000
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Polar data table (+)
Polar graphs
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