GOE 693 AIRFOIL (goe693-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 693 AIRFOIL (goe693-il) Reynolds number: 100,000 Max Cl/Cd: 55.98 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe693-il-100000.txt Download as CSV file: xf-goe693-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 693 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3583 0.10464 0.09947 -0.0388 1.0000 0.1303
-9.000 -0.3939 0.10351 0.09852 -0.0418 1.0000 0.1326
-8.750 -0.4304 0.10236 0.09756 -0.0417 1.0000 0.1330
-8.500 -0.3740 0.09599 0.09104 -0.0381 1.0000 0.1369
-8.250 -0.3730 0.09372 0.08882 -0.0362 1.0000 0.1397
-8.000 -0.3839 0.09183 0.08703 -0.0344 1.0000 0.1426
-7.750 -0.4089 0.09058 0.08591 -0.0316 1.0000 0.1450
-7.500 -0.4455 0.08973 0.08522 -0.0288 1.0000 0.1466
-7.250 -0.5051 0.08833 0.08388 -0.0325 1.0000 0.1486
-7.000 -0.5093 0.08459 0.08020 -0.0301 1.0000 0.1497
-6.750 -0.5026 0.08234 0.07803 -0.0254 1.0000 0.1511
-6.500 -0.5022 0.08049 0.07622 -0.0222 1.0000 0.1532
-6.250 -0.4964 0.07790 0.07362 -0.0226 0.9983 0.1581
-6.000 -0.4737 0.07192 0.06750 -0.0319 0.9911 0.1684
-5.750 -0.4476 0.06678 0.06210 -0.0409 0.9838 0.1823
-5.500 -0.4227 0.04850 0.04265 -0.0536 0.9772 0.1149
-5.250 -0.3918 0.04322 0.03689 -0.0574 0.9721 0.1119
-5.000 -0.3606 0.03878 0.03183 -0.0603 0.9669 0.1113
-4.750 -0.3293 0.03538 0.02786 -0.0623 0.9610 0.1117
-4.500 -0.2912 0.03285 0.02470 -0.0650 0.9570 0.1154
-4.250 -0.2605 0.03100 0.02244 -0.0663 0.9512 0.1202
-4.000 -0.2270 0.02986 0.02121 -0.0679 0.9453 0.1256
-3.750 -0.1859 0.02851 0.01939 -0.0706 0.9415 0.1345
-3.500 -0.1590 0.02786 0.01878 -0.0710 0.9347 0.1434
-3.250 -0.1240 0.02695 0.01772 -0.0727 0.9293 0.1548
-3.000 -0.0827 0.02622 0.01693 -0.0755 0.9256 0.1708
-2.750 -0.0588 0.02586 0.01651 -0.0751 0.9180 0.1843
-2.500 -0.0229 0.02538 0.01604 -0.0770 0.9130 0.2013
-2.250 0.0194 0.02486 0.01557 -0.0799 0.9096 0.2203
-2.000 0.0390 0.02475 0.01547 -0.0788 0.9010 0.2343
-1.750 0.0769 0.02432 0.01514 -0.0809 0.8965 0.2550
-1.500 0.1104 0.02402 0.01490 -0.0821 0.8912 0.2786
-1.250 0.1364 0.02372 0.01484 -0.0821 0.8841 0.3080
-1.000 0.1767 0.02273 0.01447 -0.0845 0.8803 0.4023
-0.750 0.2522 0.02079 0.01415 -0.0915 0.8794 1.0000
-0.500 0.2764 0.02091 0.01407 -0.0907 0.8683 1.0000
-0.250 0.3309 0.02031 0.01325 -0.0949 0.8632 1.0000
0.000 0.3528 0.02043 0.01324 -0.0936 0.8517 1.0000
0.250 0.3967 0.02007 0.01273 -0.0960 0.8474 1.0000
0.500 0.4127 0.02050 0.01308 -0.0940 0.8367 1.0000
0.750 0.4524 0.02022 0.01270 -0.0956 0.8323 1.0000
1.000 0.4702 0.02064 0.01306 -0.0940 0.8219 1.0000
1.250 0.5081 0.02035 0.01270 -0.0952 0.8169 1.0000
1.500 0.5278 0.02071 0.01302 -0.0937 0.8065 1.0000
1.750 0.5654 0.02034 0.01259 -0.0947 0.8010 1.0000
2.000 0.5865 0.02061 0.01283 -0.0933 0.7900 1.0000
2.250 0.6248 0.02012 0.01229 -0.0942 0.7843 1.0000
2.500 0.6457 0.02036 0.01253 -0.0927 0.7723 1.0000
2.750 0.6734 0.02029 0.01243 -0.0920 0.7622 1.0000
3.000 0.7072 0.01986 0.01196 -0.0921 0.7534 1.0000
3.250 0.7309 0.01992 0.01203 -0.0908 0.7407 1.0000
3.500 0.7576 0.01986 0.01196 -0.0900 0.7291 1.0000
3.750 0.7914 0.01948 0.01153 -0.0900 0.7202 1.0000
4.000 0.8148 0.01959 0.01167 -0.0888 0.7066 1.0000
4.250 0.8396 0.01964 0.01173 -0.0877 0.6931 1.0000
4.500 0.8656 0.01960 0.01171 -0.0868 0.6793 1.0000
4.750 0.8920 0.01956 0.01168 -0.0859 0.6653 1.0000
5.000 0.9185 0.01952 0.01164 -0.0851 0.6509 1.0000
5.250 0.9443 0.01947 0.01159 -0.0841 0.6350 1.0000
5.500 0.9693 0.01943 0.01156 -0.0831 0.6179 1.0000
5.750 0.9941 0.01942 0.01155 -0.0820 0.6004 1.0000
6.000 1.0188 0.01944 0.01156 -0.0809 0.5826 1.0000
6.250 1.0435 0.01948 0.01159 -0.0799 0.5646 1.0000
6.500 1.0681 0.01955 0.01163 -0.0789 0.5466 1.0000
6.750 1.0893 0.01979 0.01189 -0.0774 0.5264 1.0000
7.000 1.1113 0.02002 0.01212 -0.0761 0.5062 1.0000
7.250 1.1336 0.02025 0.01230 -0.0748 0.4859 1.0000
7.500 1.1534 0.02063 0.01265 -0.0732 0.4635 1.0000
7.750 1.1732 0.02106 0.01302 -0.0716 0.4412 1.0000
8.000 1.1919 0.02162 0.01351 -0.0699 0.4180 1.0000
8.250 1.2099 0.02228 0.01410 -0.0682 0.3945 1.0000
8.500 1.2275 0.02308 0.01482 -0.0664 0.3713 1.0000
8.750 1.2446 0.02395 0.01562 -0.0647 0.3488 1.0000
9.000 1.2632 0.02488 0.01640 -0.0633 0.3287 1.0000
9.250 1.2759 0.02571 0.01729 -0.0609 0.3085 1.0000
9.500 1.2864 0.02644 0.01805 -0.0583 0.2889 1.0000
9.750 1.2942 0.02712 0.01873 -0.0552 0.2703 1.0000
10.000 1.3000 0.02784 0.01944 -0.0520 0.2529 1.0000
10.250 1.3034 0.02864 0.02023 -0.0484 0.2370 1.0000
10.500 1.3071 0.02961 0.02122 -0.0452 0.2216 1.0000
10.750 1.3111 0.03075 0.02237 -0.0422 0.2065 1.0000
11.000 1.3146 0.03210 0.02368 -0.0395 0.1918 1.0000
11.250 1.3172 0.03367 0.02522 -0.0368 0.1767 1.0000
11.500 1.3177 0.03545 0.02701 -0.0342 0.1609 1.0000
11.750 1.3144 0.03749 0.02911 -0.0315 0.1436 1.0000
12.000 1.3072 0.03983 0.03151 -0.0290 0.1247 1.0000
12.250 1.2988 0.04253 0.03414 -0.0269 0.1074 1.0000
12.500 1.2928 0.04539 0.03693 -0.0251 0.0939 1.0000
12.750 1.2895 0.04818 0.03954 -0.0233 0.0847 1.0000
13.000 1.2926 0.05065 0.04211 -0.0217 0.0773 1.0000
13.250 1.2997 0.05293 0.04428 -0.0200 0.0718 1.0000
13.500 1.3044 0.05531 0.04685 -0.0188 0.0673 1.0000
13.750 1.3133 0.05738 0.04882 -0.0177 0.0633 1.0000
14.000 1.3231 0.05974 0.05133 -0.0164 0.0604 1.0000
14.250 1.3290 0.06234 0.05418 -0.0153 0.0583 1.0000
14.500 1.3348 0.06495 0.05695 -0.0144 0.0563 1.0000
14.750 1.3429 0.06735 0.05939 -0.0136 0.0544 1.0000
15.000 1.3551 0.07008 0.06213 -0.0127 0.0525 1.0000
15.250 1.3459 0.07393 0.06631 -0.0121 0.0517 1.0000
15.500 1.3352 0.07811 0.07080 -0.0120 0.0510 1.0000
15.750 1.3227 0.08267 0.07564 -0.0121 0.0505 1.0000
16.000 1.3077 0.08771 0.08097 -0.0128 0.0501 1.0000
16.250 1.2895 0.09339 0.08693 -0.0141 0.0500 1.0000
16.500 1.2680 0.09982 0.09363 -0.0162 0.0501 1.0000
16.750 1.2431 0.10718 0.10126 -0.0194 0.0503 1.0000
17.000 1.2152 0.11564 0.10998 -0.0238 0.0507 1.0000
17.250 1.1846 0.12537 0.11994 -0.0295 0.0512 1.0000
17.500 1.1521 0.13651 0.13127 -0.0365 0.0519 1.0000
17.750 1.1213 0.14837 0.14326 -0.0440 0.0526 1.0000
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