GIII BL430 AIRFOIL (giiim-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL430 AIRFOIL (giiim-il) Reynolds number: 200,000 Max Cl/Cd: 52.24 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiim-il-200000-n5.txt Download as CSV file: xf-giiim-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL430 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5383 0.09352 0.08982 0.0012 1.0000 0.0315
-8.250 -0.5414 0.08811 0.08445 -0.0058 1.0000 0.0317
-8.000 -0.5422 0.08268 0.07896 -0.0122 1.0000 0.0318
-7.750 -0.5384 0.07779 0.07400 -0.0160 1.0000 0.0318
-7.500 -0.5320 0.07333 0.06944 -0.0184 1.0000 0.0318
-7.250 -0.5236 0.06910 0.06511 -0.0201 1.0000 0.0318
-7.000 -0.5136 0.06506 0.06096 -0.0213 1.0000 0.0318
-6.500 -0.4933 0.05652 0.05234 -0.0218 1.0000 0.0268
-6.250 -0.4800 0.05335 0.04908 -0.0221 1.0000 0.0263
-6.000 -0.4657 0.04976 0.04534 -0.0223 1.0000 0.0258
-5.750 -0.4505 0.04615 0.04155 -0.0223 1.0000 0.0255
-5.500 -0.4345 0.04274 0.03792 -0.0218 1.0000 0.0254
-5.250 -0.4179 0.03939 0.03430 -0.0208 1.0000 0.0263
-5.000 -0.4023 0.03493 0.02935 -0.0189 1.0000 0.0271
-4.750 -0.3866 0.03246 0.02668 -0.0173 1.0000 0.0273
-4.500 -0.3555 0.03056 0.02466 -0.0191 0.9919 0.0278
-4.250 -0.3235 0.02846 0.02234 -0.0205 0.9823 0.0284
-4.000 -0.2911 0.02653 0.02018 -0.0218 0.9724 0.0296
-3.750 -0.2586 0.02377 0.01692 -0.0223 0.9621 0.0314
-3.500 -0.2271 0.02159 0.01437 -0.0228 0.9510 0.0321
-3.250 -0.1956 0.02071 0.01347 -0.0238 0.9395 0.0330
-3.000 -0.1639 0.01981 0.01244 -0.0246 0.9272 0.0347
-2.750 -0.1329 0.01851 0.01090 -0.0247 0.9142 0.0359
-2.500 -0.1037 0.01735 0.00949 -0.0245 0.9000 0.0368
-2.250 -0.0757 0.01648 0.00850 -0.0242 0.8859 0.0379
-2.000 -0.0486 0.01596 0.00799 -0.0238 0.8716 0.0393
-1.750 -0.0218 0.01536 0.00731 -0.0233 0.8572 0.0406
-1.500 0.0045 0.01474 0.00660 -0.0225 0.8422 0.0416
-1.250 0.0305 0.01420 0.00597 -0.0217 0.8263 0.0427
-1.000 0.0562 0.01374 0.00546 -0.0210 0.8100 0.0443
-0.750 0.0818 0.01335 0.00510 -0.0203 0.7936 0.0460
-0.500 0.1073 0.01299 0.00471 -0.0195 0.7749 0.0475
-0.250 0.1326 0.01267 0.00433 -0.0186 0.7519 0.0491
0.000 0.1578 0.01244 0.00400 -0.0177 0.7234 0.0508
0.250 0.1822 0.01216 0.00366 -0.0168 0.6892 0.0536
0.500 0.2073 0.01202 0.00340 -0.0160 0.6565 0.0565
0.750 0.2330 0.01194 0.00317 -0.0153 0.6298 0.0592
1.000 0.2590 0.01183 0.00298 -0.0148 0.6074 0.0634
1.250 0.2853 0.01182 0.00287 -0.0143 0.5857 0.0696
1.500 0.3115 0.01180 0.00277 -0.0138 0.5645 0.0783
1.750 0.3363 0.01144 0.00271 -0.0132 0.5429 0.2225
2.000 0.3502 0.00958 0.00293 -0.0096 0.5238 0.9055
2.250 0.4079 0.00974 0.00298 -0.0153 0.4937 0.9901
2.500 0.4436 0.00990 0.00301 -0.0170 0.4686 1.0000
2.750 0.4680 0.01009 0.00306 -0.0163 0.4451 1.0000
3.000 0.4926 0.01028 0.00314 -0.0156 0.4184 1.0000
3.250 0.5167 0.01051 0.00322 -0.0149 0.3830 1.0000
3.500 0.5402 0.01085 0.00332 -0.0141 0.3317 1.0000
4.000 0.5867 0.01174 0.00374 -0.0126 0.2476 1.0000
4.250 0.6105 0.01217 0.00400 -0.0120 0.2205 1.0000
4.500 0.6347 0.01255 0.00427 -0.0114 0.1991 1.0000
4.750 0.6591 0.01292 0.00456 -0.0108 0.1794 1.0000
5.000 0.6835 0.01331 0.00486 -0.0103 0.1607 1.0000
5.250 0.7079 0.01371 0.00517 -0.0098 0.1445 1.0000
5.500 0.7323 0.01412 0.00552 -0.0092 0.1303 1.0000
5.750 0.7568 0.01454 0.00588 -0.0087 0.1188 1.0000
6.000 0.7811 0.01498 0.00628 -0.0082 0.1093 1.0000
6.250 0.8052 0.01545 0.00671 -0.0077 0.1008 1.0000
6.500 0.8296 0.01588 0.00716 -0.0072 0.0939 1.0000
6.750 0.8533 0.01641 0.00764 -0.0067 0.0875 1.0000
7.000 0.8776 0.01686 0.00813 -0.0062 0.0822 1.0000
7.250 0.9012 0.01739 0.00866 -0.0057 0.0771 1.0000
7.500 0.9247 0.01794 0.00923 -0.0051 0.0726 1.0000
7.750 0.9483 0.01846 0.00980 -0.0046 0.0684 1.0000
8.000 0.9706 0.01915 0.01047 -0.0040 0.0649 1.0000
8.250 0.9939 0.01971 0.01111 -0.0034 0.0616 1.0000
8.500 1.0166 0.02031 0.01176 -0.0028 0.0584 1.0000
8.750 1.0379 0.02108 0.01252 -0.0022 0.0558 1.0000
9.000 1.0599 0.02179 0.01333 -0.0015 0.0536 1.0000
9.250 1.0816 0.02250 0.01412 -0.0008 0.0512 1.0000
9.500 1.1027 0.02323 0.01490 -0.0002 0.0492 1.0000
9.750 1.1218 0.02419 0.01585 0.0006 0.0474 1.0000
10.000 1.1423 0.02502 0.01682 0.0014 0.0458 1.0000
10.250 1.1617 0.02594 0.01786 0.0022 0.0444 1.0000
10.500 1.1805 0.02688 0.01890 0.0030 0.0430 1.0000
10.750 1.1985 0.02782 0.01991 0.0039 0.0418 1.0000
11.000 1.2148 0.02891 0.02103 0.0048 0.0407 1.0000
11.250 1.2304 0.03012 0.02236 0.0059 0.0396 1.0000
11.500 1.2456 0.03131 0.02374 0.0069 0.0386 1.0000
11.750 1.2591 0.03258 0.02517 0.0081 0.0376 1.0000
12.000 1.2705 0.03390 0.02662 0.0094 0.0368 1.0000
12.250 1.2795 0.03527 0.02811 0.0109 0.0361 1.0000
12.500 1.2871 0.03674 0.02969 0.0122 0.0355 1.0000
12.750 1.2933 0.03837 0.03141 0.0133 0.0350 1.0000
13.000 1.2981 0.04022 0.03334 0.0143 0.0345 1.0000
13.250 1.3009 0.04241 0.03563 0.0150 0.0340 1.0000
13.500 1.3003 0.04500 0.03847 0.0153 0.0336 1.0000
13.750 1.2977 0.04797 0.04168 0.0151 0.0331 1.0000
14.000 1.2931 0.05135 0.04528 0.0145 0.0326 1.0000
14.250 1.2865 0.05520 0.04936 0.0132 0.0322 1.0000
14.500 1.2776 0.05960 0.05397 0.0113 0.0319 1.0000
14.750 1.2661 0.06465 0.05922 0.0088 0.0316 1.0000
15.000 1.2512 0.07050 0.06528 0.0056 0.0314 1.0000
15.250 1.2317 0.07738 0.07238 0.0015 0.0313 1.0000
15.500 1.2059 0.08577 0.08098 -0.0036 0.0312 1.0000
15.750 1.1675 0.09726 0.09272 -0.0109 0.0313 1.0000
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Polar data table (+)
Polar graphs
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