GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 488 AIRFOIL (goe488-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.4 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe488-il-1000000-n5.txt Download as CSV file: xf-goe488-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 488 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4962 0.11305 0.11135 -0.0183 1.0000 0.0067
-11.250 -0.5109 0.10530 0.10360 -0.0214 1.0000 0.0077
-10.250 -0.7818 0.02028 0.01688 -0.0710 0.9886 0.0077
-10.000 -0.7572 0.01809 0.01443 -0.0719 0.9869 0.0088
-9.750 -0.7326 0.01649 0.01262 -0.0722 0.9846 0.0099
-9.500 -0.7069 0.01544 0.01140 -0.0724 0.9819 0.0114
-9.250 -0.6767 0.01529 0.01131 -0.0730 0.9803 0.0134
-9.000 -0.6463 0.01498 0.01095 -0.0738 0.9788 0.0151
-8.750 -0.6135 0.01528 0.01133 -0.0748 0.9777 0.0161
-8.500 -0.5812 0.01574 0.01189 -0.0755 0.9762 0.0170
-8.250 -0.5523 0.01586 0.01202 -0.0757 0.9729 0.0178
-8.000 -0.5221 0.01585 0.01199 -0.0763 0.9705 0.0188
-7.750 -0.4911 0.01572 0.01182 -0.0770 0.9685 0.0197
-7.500 -0.4611 0.01555 0.01161 -0.0776 0.9659 0.0205
-7.250 -0.4331 0.01530 0.01129 -0.0778 0.9618 0.0210
-7.000 -0.4026 0.01523 0.01117 -0.0783 0.9586 0.0214
-6.750 -0.3730 0.01520 0.01111 -0.0788 0.9544 0.0217
-6.500 -0.3438 0.01514 0.01101 -0.0790 0.9482 0.0219
-6.250 -0.3209 0.01329 0.00884 -0.0787 0.9397 0.0231
-6.000 -0.2939 0.01278 0.00824 -0.0787 0.9309 0.0237
-5.750 -0.2672 0.01248 0.00786 -0.0784 0.9230 0.0242
-5.500 -0.2408 0.01212 0.00742 -0.0782 0.9147 0.0246
-5.250 -0.2146 0.01167 0.00686 -0.0778 0.9062 0.0250
-5.000 -0.1888 0.01120 0.00629 -0.0774 0.8972 0.0252
-4.750 -0.1627 0.01076 0.00574 -0.0770 0.8897 0.0254
-4.500 -0.1369 0.01030 0.00518 -0.0765 0.8811 0.0256
-4.250 -0.1110 0.00987 0.00465 -0.0761 0.8723 0.0258
-3.750 -0.0591 0.00912 0.00373 -0.0751 0.8544 0.0260
-3.500 -0.0329 0.00883 0.00336 -0.0747 0.8474 0.0262
-3.250 -0.0064 0.00858 0.00307 -0.0743 0.8403 0.0265
-3.000 0.0197 0.00829 0.00270 -0.0738 0.8327 0.0266
-2.750 0.0458 0.00803 0.00237 -0.0733 0.8234 0.0267
-2.500 0.0720 0.00781 0.00209 -0.0729 0.8144 0.0268
-2.250 0.0981 0.00763 0.00185 -0.0724 0.8047 0.0270
-2.000 0.1246 0.00747 0.00164 -0.0720 0.7941 0.0273
-1.750 0.1508 0.00734 0.00146 -0.0715 0.7817 0.0278
-1.500 0.1768 0.00725 0.00131 -0.0710 0.7648 0.0285
-1.250 0.2022 0.00722 0.00119 -0.0703 0.7390 0.0295
-1.000 0.2263 0.00729 0.00110 -0.0694 0.6964 0.0303
-0.750 0.2497 0.00744 0.00105 -0.0684 0.6475 0.0309
-0.500 0.2739 0.00759 0.00105 -0.0675 0.6078 0.0312
-0.250 0.2985 0.00768 0.00100 -0.0668 0.5712 0.0323
0.000 0.3221 0.00788 0.00097 -0.0659 0.5130 0.0338
0.250 0.3448 0.00818 0.00100 -0.0649 0.4393 0.0359
0.500 0.3686 0.00843 0.00105 -0.0641 0.3865 0.0384
0.750 0.3934 0.00859 0.00109 -0.0635 0.3513 0.0421
1.000 0.4187 0.00867 0.00113 -0.0630 0.3282 0.0600
1.250 0.4441 0.00864 0.00118 -0.0625 0.3129 0.1113
1.500 0.4696 0.00860 0.00125 -0.0620 0.3012 0.1702
1.750 0.4951 0.00852 0.00133 -0.0616 0.2910 0.2468
2.000 0.5206 0.00843 0.00141 -0.0612 0.2818 0.3206
2.250 0.5283 0.00699 0.00156 -0.0570 0.2739 0.9189
2.500 0.5774 0.00708 0.00168 -0.0617 0.2623 0.9742
2.750 0.6252 0.00724 0.00178 -0.0663 0.2499 0.9920
3.000 0.6613 0.00741 0.00187 -0.0682 0.2360 0.9982
3.250 0.6902 0.00772 0.00200 -0.0686 0.1989 1.0000
3.500 0.7105 0.00812 0.00220 -0.0672 0.1574 1.0000
3.750 0.7329 0.00838 0.00236 -0.0660 0.1384 1.0000
4.000 0.7552 0.00865 0.00254 -0.0649 0.1190 1.0000
4.250 0.7771 0.00898 0.00275 -0.0638 0.0965 1.0000
4.500 0.7974 0.00949 0.00304 -0.0623 0.0561 1.0000
4.750 0.8207 0.00973 0.00325 -0.0614 0.0477 1.0000
5.000 0.8441 0.00995 0.00345 -0.0605 0.0412 1.0000
5.250 0.8654 0.01041 0.00377 -0.0593 0.0193 1.0000
5.500 0.8889 0.01066 0.00402 -0.0584 0.0139 1.0000
5.750 0.9123 0.01094 0.00432 -0.0575 0.0119 1.0000
6.000 0.9354 0.01125 0.00465 -0.0566 0.0101 1.0000
6.250 0.9588 0.01154 0.00498 -0.0557 0.0092 1.0000
6.500 0.9823 0.01182 0.00529 -0.0549 0.0086 1.0000
6.750 1.0056 0.01213 0.00562 -0.0540 0.0080 1.0000
7.000 1.0286 0.01245 0.00596 -0.0532 0.0073 1.0000
7.250 1.0511 0.01285 0.00638 -0.0522 0.0067 1.0000
7.500 1.0728 0.01334 0.00693 -0.0512 0.0062 1.0000
7.750 1.0955 0.01370 0.00733 -0.0503 0.0059 1.0000
8.000 1.1177 0.01412 0.00779 -0.0493 0.0057 1.0000
8.250 1.1395 0.01457 0.00828 -0.0483 0.0054 1.0000
8.500 1.1611 0.01501 0.00876 -0.0473 0.0051 1.0000
8.750 1.1823 0.01548 0.00928 -0.0462 0.0049 1.0000
9.000 1.2031 0.01599 0.00984 -0.0451 0.0047 1.0000
9.250 1.2233 0.01652 0.01042 -0.0439 0.0045 1.0000
9.500 1.2399 0.01739 0.01136 -0.0422 0.0041 1.0000
9.750 1.2591 0.01796 0.01199 -0.0409 0.0040 1.0000
10.000 1.2783 0.01850 0.01259 -0.0396 0.0039 1.0000
10.250 1.2955 0.01918 0.01336 -0.0380 0.0037 1.0000
10.500 1.3117 0.01991 0.01416 -0.0362 0.0036 1.0000
10.750 1.3271 0.02064 0.01498 -0.0344 0.0035 1.0000
11.000 1.3404 0.02148 0.01590 -0.0323 0.0034 1.0000
11.250 1.3513 0.02227 0.01680 -0.0297 0.0033 1.0000
11.500 1.3615 0.02304 0.01765 -0.0270 0.0032 1.0000
11.750 1.3720 0.02380 0.01848 -0.0246 0.0031 1.0000
12.000 1.3792 0.02478 0.01956 -0.0218 0.0031 1.0000
12.250 1.3892 0.02561 0.02044 -0.0195 0.0030 1.0000
12.500 1.3929 0.02688 0.02183 -0.0167 0.0029 1.0000
12.750 1.4014 0.02785 0.02288 -0.0146 0.0029 1.0000
13.000 1.4048 0.02923 0.02436 -0.0122 0.0029 1.0000
13.250 1.4055 0.03090 0.02614 -0.0097 0.0028 1.0000
13.500 1.4102 0.03232 0.02764 -0.0080 0.0027 1.0000
13.750 1.4091 0.03431 0.02975 -0.0061 0.0027 1.0000
14.000 1.4052 0.03671 0.03228 -0.0044 0.0027 1.0000
14.250 1.3985 0.03959 0.03531 -0.0032 0.0027 1.0000
14.500 1.3883 0.04309 0.03897 -0.0025 0.0026 1.0000
14.750 1.3732 0.04758 0.04363 -0.0027 0.0025 1.0000
15.000 1.3650 0.05172 0.04791 -0.0037 0.0025 1.0000
15.250 1.3520 0.05696 0.05331 -0.0056 0.0025 1.0000
15.500 1.3357 0.06323 0.05973 -0.0084 0.0025 1.0000
15.750 1.3213 0.06971 0.06637 -0.0118 0.0025 1.0000
16.000 1.3034 0.07719 0.07400 -0.0158 0.0025 1.0000
16.250 1.2925 0.08353 0.08046 -0.0192 0.0025 1.0000
16.500 1.2676 0.09239 0.08947 -0.0238 0.0025 1.0000
16.750 1.2541 0.09930 0.09649 -0.0275 0.0025 1.0000
17.250 1.2137 0.11601 0.11342 -0.0363 0.0025 1.0000
17.500 1.1944 0.12464 0.12217 -0.0410 0.0025 1.0000
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