GIII BL0 AIRFOIL (giiia-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL0 AIRFOIL (giiia-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.01 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiia-il-1000000-n5.txt Download as CSV file: xf-giiia-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL0 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
------ -------- --------- --------- -------- -------- --------
-16.250 -1.0345 0.09815 0.09607 -0.0027 1.0000 0.0034
-16.000 -1.1787 0.06128 0.05870 -0.0260 1.0000 0.0033
-15.750 -1.2066 0.05312 0.05033 -0.0309 1.0000 0.0032
-15.500 -1.2240 0.04762 0.04465 -0.0331 1.0000 0.0033
-15.250 -1.2355 0.04349 0.04036 -0.0339 1.0000 0.0033
-15.000 -1.2442 0.04010 0.03681 -0.0337 1.0000 0.0033
-14.750 -1.2487 0.03742 0.03397 -0.0328 1.0000 0.0033
-14.500 -1.2512 0.03512 0.03153 -0.0314 1.0000 0.0033
-14.250 -1.2512 0.03316 0.02943 -0.0297 1.0000 0.0034
-14.000 -1.2489 0.03147 0.02761 -0.0278 1.0000 0.0034
-13.750 -1.2449 0.02997 0.02598 -0.0257 1.0000 0.0034
-13.500 -1.2411 0.02848 0.02436 -0.0233 1.0000 0.0034
-13.250 -1.2393 0.02685 0.02255 -0.0204 1.0000 0.0036
-13.000 -1.2334 0.02551 0.02107 -0.0177 1.0000 0.0037
-12.750 -1.2240 0.02439 0.01984 -0.0154 1.0000 0.0038
-12.500 -1.2116 0.02343 0.01878 -0.0134 1.0000 0.0039
-12.250 -1.1963 0.02255 0.01780 -0.0118 1.0000 0.0040
-12.000 -1.1797 0.02175 0.01691 -0.0104 1.0000 0.0042
-11.750 -1.1622 0.02099 0.01607 -0.0091 1.0000 0.0043
-11.500 -1.1440 0.02029 0.01529 -0.0078 1.0000 0.0045
-11.250 -1.1252 0.01961 0.01454 -0.0066 1.0000 0.0046
-11.000 -1.1061 0.01896 0.01381 -0.0054 1.0000 0.0048
-10.750 -1.0867 0.01834 0.01311 -0.0042 1.0000 0.0050
-10.500 -1.0670 0.01775 0.01245 -0.0029 1.0000 0.0051
-10.250 -1.0472 0.01720 0.01182 -0.0017 1.0000 0.0053
-10.000 -1.0273 0.01670 0.01125 -0.0004 1.0000 0.0054
-9.750 -1.0091 0.01610 0.01058 0.0012 1.0000 0.0057
-9.500 -0.9910 0.01558 0.01002 0.0029 1.0000 0.0061
-9.250 -0.9726 0.01517 0.00959 0.0045 1.0000 0.0065
-9.000 -0.9456 0.01473 0.00912 0.0043 0.9981 0.0070
-8.750 -0.9161 0.01429 0.00864 0.0036 0.9956 0.0075
-8.500 -0.8865 0.01386 0.00816 0.0029 0.9931 0.0079
-8.250 -0.8576 0.01344 0.00768 0.0024 0.9896 0.0082
-8.000 -0.8287 0.01292 0.00713 0.0018 0.9864 0.0091
-7.750 -0.7994 0.01253 0.00673 0.0012 0.9821 0.0099
-7.500 -0.7690 0.01217 0.00635 0.0004 0.9762 0.0106
-7.250 -0.7392 0.01185 0.00599 -0.0002 0.9675 0.0113
-7.000 -0.7110 0.01153 0.00562 -0.0004 0.9572 0.0121
-6.750 -0.6851 0.01118 0.00523 -0.0001 0.9458 0.0135
-6.500 -0.6601 0.01091 0.00493 0.0004 0.9344 0.0147
-6.250 -0.6351 0.01066 0.00465 0.0010 0.9242 0.0158
-6.000 -0.6096 0.01045 0.00439 0.0014 0.9163 0.0166
-5.750 -0.5846 0.01017 0.00409 0.0019 0.9085 0.0193
-5.500 -0.5591 0.00994 0.00384 0.0024 0.9020 0.0216
-5.250 -0.5331 0.00975 0.00362 0.0027 0.8953 0.0234
-5.000 -0.5075 0.00953 0.00338 0.0031 0.8890 0.0276
-4.750 -0.4816 0.00932 0.00317 0.0035 0.8822 0.0313
-4.250 -0.4295 0.00894 0.00278 0.0042 0.8688 0.0426
-4.000 -0.4040 0.00874 0.00259 0.0046 0.8600 0.0539
-3.750 -0.3786 0.00854 0.00241 0.0051 0.8484 0.0677
-3.500 -0.3532 0.00833 0.00224 0.0055 0.8363 0.0853
-3.250 -0.3278 0.00812 0.00208 0.0060 0.8245 0.1092
-3.000 -0.3026 0.00791 0.00194 0.0065 0.8108 0.1369
-2.750 -0.2771 0.00774 0.00181 0.0069 0.7940 0.1612
-2.500 -0.2515 0.00763 0.00169 0.0074 0.7694 0.1799
-2.250 -0.2276 0.00759 0.00155 0.0082 0.7197 0.2033
-2.000 -0.2046 0.00750 0.00144 0.0091 0.6752 0.2439
-1.750 -0.1829 0.00728 0.00132 0.0102 0.6320 0.3157
-1.500 -0.1649 0.00670 0.00113 0.0119 0.5971 0.4584
-1.250 -0.1455 0.00630 0.00105 0.0134 0.5698 0.5774
-1.000 -0.1212 0.00622 0.00101 0.0141 0.5469 0.6171
-0.750 -0.0963 0.00618 0.00099 0.0147 0.5256 0.6459
-0.500 -0.0712 0.00615 0.00096 0.0153 0.5064 0.6712
-0.250 -0.0459 0.00611 0.00095 0.0158 0.4895 0.6956
0.000 -0.0207 0.00610 0.00094 0.0164 0.4702 0.7200
0.250 0.0042 0.00608 0.00094 0.0170 0.4486 0.7461
0.500 0.0284 0.00609 0.00095 0.0178 0.4192 0.7747
0.750 0.0521 0.00617 0.00099 0.0186 0.3793 0.8049
1.000 0.0765 0.00628 0.00106 0.0193 0.3445 0.8320
1.250 0.1011 0.00647 0.00115 0.0200 0.2984 0.8542
1.500 0.1258 0.00672 0.00126 0.0205 0.2501 0.8730
1.750 0.1519 0.00689 0.00137 0.0209 0.2255 0.8880
2.250 0.2058 0.00715 0.00153 0.0212 0.1967 0.9048
2.500 0.2337 0.00726 0.00162 0.0211 0.1884 0.9108
2.750 0.2609 0.00738 0.00172 0.0212 0.1811 0.9173
3.000 0.2887 0.00748 0.00181 0.0212 0.1765 0.9226
3.250 0.3168 0.00759 0.00191 0.0211 0.1723 0.9276
3.500 0.3439 0.00771 0.00202 0.0212 0.1683 0.9331
3.750 0.3720 0.00783 0.00214 0.0210 0.1648 0.9373
4.000 0.4007 0.00793 0.00226 0.0208 0.1630 0.9413
4.250 0.4281 0.00804 0.00239 0.0208 0.1609 0.9459
4.500 0.4553 0.00817 0.00251 0.0209 0.1583 0.9500
4.750 0.4847 0.00831 0.00266 0.0205 0.1557 0.9528
5.000 0.5132 0.00846 0.00282 0.0202 0.1534 0.9561
5.250 0.5400 0.00860 0.00298 0.0203 0.1499 0.9600
5.500 0.5675 0.00871 0.00310 0.0203 0.1457 0.9632
5.750 0.5974 0.00889 0.00326 0.0197 0.1399 0.9651
6.000 0.6267 0.00904 0.00342 0.0192 0.1345 0.9674
6.250 0.6549 0.00924 0.00358 0.0189 0.1242 0.9701
6.500 0.6805 0.00945 0.00375 0.0192 0.1116 0.9737
6.750 0.7041 0.01037 0.00431 0.0193 0.0482 0.9759
7.000 0.7323 0.01097 0.00480 0.0188 0.0257 0.9778
7.250 0.7630 0.01138 0.00520 0.0178 0.0185 0.9803
7.500 0.7923 0.01178 0.00559 0.0171 0.0143 0.9838
7.750 0.8235 0.01212 0.00595 0.0161 0.0126 0.9858
8.000 0.8543 0.01253 0.00636 0.0150 0.0105 0.9868
8.250 0.8837 0.01289 0.00675 0.0143 0.0093 0.9878
8.500 0.9125 0.01326 0.00715 0.0136 0.0083 0.9889
8.750 0.9403 0.01368 0.00759 0.0132 0.0074 0.9903
9.000 0.9671 0.01418 0.00813 0.0129 0.0066 0.9919
9.250 0.9937 0.01459 0.00859 0.0127 0.0063 0.9935
9.500 1.0203 0.01504 0.00908 0.0124 0.0059 0.9947
9.750 1.0480 0.01552 0.00961 0.0119 0.0055 0.9956
10.000 1.0753 0.01603 0.01017 0.0113 0.0052 0.9966
10.250 1.1019 0.01661 0.01080 0.0109 0.0048 0.9978
10.500 1.1264 0.01743 0.01170 0.0107 0.0043 0.9991
10.750 1.1518 0.01797 0.01229 0.0105 0.0042 1.0000
11.000 1.1649 0.01846 0.01284 0.0129 0.0041 1.0000
11.250 1.1771 0.01899 0.01344 0.0154 0.0040 1.0000
11.500 1.1885 0.01956 0.01407 0.0180 0.0038 1.0000
11.750 1.1994 0.02016 0.01475 0.0207 0.0037 1.0000
12.000 1.2096 0.02080 0.01545 0.0233 0.0036 1.0000
12.250 1.2192 0.02149 0.01622 0.0260 0.0035 1.0000
12.500 1.2257 0.02217 0.01697 0.0292 0.0034 1.0000
12.750 1.2323 0.02293 0.01781 0.0321 0.0033 1.0000
13.000 1.2398 0.02382 0.01877 0.0344 0.0032 1.0000
13.250 1.2474 0.02482 0.01985 0.0365 0.0031 1.0000
13.500 1.2542 0.02597 0.02108 0.0383 0.0031 1.0000
13.750 1.2598 0.02730 0.02251 0.0399 0.0030 1.0000
14.000 1.2637 0.02887 0.02417 0.0413 0.0029 1.0000
14.250 1.2656 0.03073 0.02613 0.0424 0.0028 1.0000
14.500 1.2651 0.03299 0.02851 0.0432 0.0028 1.0000
14.750 1.2614 0.03580 0.03145 0.0433 0.0027 1.0000
15.000 1.2553 0.03926 0.03505 0.0427 0.0027 1.0000
15.250 1.2460 0.04355 0.03948 0.0411 0.0026 1.0000
15.500 1.2342 0.04862 0.04470 0.0386 0.0026 1.0000
15.750 1.2190 0.05450 0.05074 0.0356 0.0026 1.0000
16.000 1.2009 0.06107 0.05747 0.0321 0.0026 1.0000
16.250 1.1811 0.06810 0.06464 0.0284 0.0026 1.0000
16.500 1.1600 0.07554 0.07221 0.0247 0.0026 1.0000
16.750 1.1366 0.08346 0.08027 0.0208 0.0026 1.0000
17.000 1.1141 0.09132 0.08824 0.0171 0.0026 1.0000
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