HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il) Reynolds number: 500,000 Max Cl/Cd: 107.55 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq300gd2-il-500000.txt Download as CSV file: xf-hq300gd2-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3843 0.05527 0.05180 -0.0926 0.7853 0.0270
-9.250 -0.4373 0.04045 0.03625 -0.0937 0.7799 0.0223
-9.000 -0.4187 0.03873 0.03452 -0.0937 0.7740 0.0208
-8.750 -0.4143 0.03381 0.02918 -0.0936 0.7680 0.0206
-8.500 -0.4037 0.02933 0.02415 -0.0933 0.7628 0.0208
-8.250 -0.3862 0.02595 0.02029 -0.0931 0.7577 0.0211
-8.000 -0.3634 0.02392 0.01790 -0.0931 0.7524 0.0215
-7.750 -0.3406 0.02165 0.01525 -0.0930 0.7478 0.0221
-7.500 -0.3159 0.02017 0.01366 -0.0931 0.7432 0.0229
-7.250 -0.2891 0.01951 0.01296 -0.0935 0.7380 0.0237
-7.000 -0.2619 0.01895 0.01232 -0.0938 0.7332 0.0249
-6.750 -0.2347 0.01829 0.01148 -0.0939 0.7290 0.0260
-6.500 -0.2068 0.01764 0.01071 -0.0941 0.7246 0.0268
-6.250 -0.1813 0.01634 0.00932 -0.0939 0.7203 0.0278
-6.000 -0.1547 0.01560 0.00856 -0.0941 0.7163 0.0289
-5.750 -0.1268 0.01523 0.00813 -0.0944 0.7123 0.0303
-5.500 -0.0985 0.01481 0.00769 -0.0948 0.7081 0.0318
-5.250 -0.0702 0.01439 0.00722 -0.0951 0.7040 0.0330
-5.000 -0.0422 0.01379 0.00655 -0.0955 0.7003 0.0341
-4.750 -0.0136 0.01324 0.00596 -0.0961 0.6968 0.0361
-4.500 0.0160 0.01292 0.00565 -0.0969 0.6931 0.0383
-4.250 0.0459 0.01261 0.00530 -0.0976 0.6892 0.0403
-4.000 0.0763 0.01219 0.00485 -0.0985 0.6855 0.0428
-3.750 0.1068 0.01191 0.00454 -0.0994 0.6823 0.0470
-3.500 0.1378 0.01165 0.00425 -0.1004 0.6791 0.0536
-3.250 0.1693 0.01129 0.00397 -0.1015 0.6756 0.0713
-3.000 0.2088 0.00978 0.00352 -0.1060 0.6720 0.3444
-2.750 0.2534 0.00860 0.00335 -0.1111 0.6687 0.6261
-2.500 0.2834 0.00868 0.00357 -0.1114 0.6656 0.6976
-2.250 0.3127 0.00885 0.00375 -0.1116 0.6625 0.7253
-2.000 0.3425 0.00904 0.00391 -0.1119 0.6590 0.7438
-1.750 0.3696 0.00935 0.00421 -0.1114 0.6556 0.7599
-1.500 0.3928 0.00971 0.00458 -0.1098 0.6525 0.7691
-1.250 0.4201 0.01000 0.00480 -0.1095 0.6495 0.7781
-1.000 0.4447 0.01024 0.00506 -0.1085 0.6464 0.7828
-0.750 0.4735 0.01035 0.00515 -0.1087 0.6430 0.7874
-0.500 0.5060 0.01040 0.00513 -0.1099 0.6396 0.7923
-0.250 0.5326 0.01050 0.00520 -0.1096 0.6365 0.7945
0.000 0.5593 0.01067 0.00532 -0.1093 0.6335 0.7970
0.250 0.5867 0.01079 0.00544 -0.1091 0.6303 0.8003
0.500 0.6158 0.01088 0.00553 -0.1095 0.6266 0.8049
0.750 0.6457 0.01095 0.00557 -0.1101 0.6228 0.8093
1.000 0.6713 0.01105 0.00564 -0.1095 0.6193 0.8116
1.250 0.6984 0.01116 0.00574 -0.1094 0.6155 0.8139
1.500 0.7266 0.01120 0.00580 -0.1096 0.6114 0.8162
1.750 0.7562 0.01123 0.00581 -0.1101 0.6073 0.8189
2.000 0.7878 0.01127 0.00581 -0.1112 0.6035 0.8219
2.250 0.8199 0.01133 0.00584 -0.1125 0.5997 0.8246
2.500 0.8472 0.01133 0.00588 -0.1125 0.5956 0.8260
2.750 0.8747 0.01137 0.00593 -0.1126 0.5914 0.8275
3.000 0.9027 0.01144 0.00597 -0.1128 0.5877 0.8293
3.250 0.9311 0.01151 0.00606 -0.1131 0.5836 0.8310
3.500 0.9599 0.01154 0.00614 -0.1136 0.5791 0.8330
3.750 0.9896 0.01158 0.00618 -0.1142 0.5747 0.8354
4.000 1.0206 0.01168 0.00623 -0.1153 0.5704 0.8377
4.250 1.0525 0.01171 0.00632 -0.1166 0.5653 0.8398
4.500 1.0793 0.01171 0.00636 -0.1165 0.5601 0.8412
4.750 1.1062 0.01180 0.00642 -0.1165 0.5551 0.8427
5.000 1.1333 0.01183 0.00654 -0.1166 0.5493 0.8442
5.250 1.1608 0.01188 0.00662 -0.1168 0.5432 0.8458
5.500 1.1885 0.01197 0.00672 -0.1171 0.5371 0.8475
5.750 1.2163 0.01203 0.00684 -0.1174 0.5298 0.8495
6.000 1.2445 0.01215 0.00695 -0.1179 0.5226 0.8517
6.250 1.2735 0.01223 0.00709 -0.1185 0.5139 0.8536
6.500 1.3023 0.01236 0.00723 -0.1192 0.5053 0.8553
6.750 1.3272 0.01247 0.00736 -0.1189 0.4953 0.8566
7.000 1.3517 0.01260 0.00754 -0.1186 0.4846 0.8582
7.250 1.3756 0.01279 0.00774 -0.1182 0.4727 0.8599
7.500 1.3992 0.01303 0.00799 -0.1177 0.4591 0.8617
7.750 1.4222 0.01331 0.00826 -0.1173 0.4436 0.8634
8.000 1.4444 0.01367 0.00859 -0.1168 0.4262 0.8653
8.250 1.4653 0.01410 0.00899 -0.1161 0.4078 0.8672
8.500 1.4845 0.01466 0.00948 -0.1152 0.3885 0.8694
8.750 1.4999 0.01522 0.00999 -0.1135 0.3694 0.8712
9.000 1.5103 0.01589 0.01060 -0.1110 0.3476 0.8730
9.250 1.5123 0.01675 0.01136 -0.1071 0.3266 0.8752
9.500 1.5204 0.01772 0.01227 -0.1047 0.3050 0.8773
9.750 1.5294 0.01876 0.01327 -0.1027 0.2872 0.8795
10.000 1.5397 0.01984 0.01432 -0.1011 0.2727 0.8819
10.250 1.5500 0.02103 0.01550 -0.0997 0.2587 0.8841
10.500 1.5579 0.02231 0.01676 -0.0980 0.2452 0.8859
10.750 1.5643 0.02373 0.01818 -0.0963 0.2315 0.8876
11.000 1.5699 0.02531 0.01974 -0.0947 0.2179 0.8895
11.250 1.5750 0.02702 0.02144 -0.0932 0.2040 0.8914
11.500 1.5792 0.02887 0.02327 -0.0918 0.1904 0.8934
11.750 1.5824 0.03088 0.02526 -0.0905 0.1768 0.8956
12.000 1.5849 0.03302 0.02737 -0.0892 0.1633 0.8977
12.250 1.5864 0.03523 0.02955 -0.0879 0.1501 0.8993
12.500 1.5862 0.03752 0.03183 -0.0865 0.1372 0.9009
12.750 1.5851 0.03995 0.03424 -0.0851 0.1246 0.9026
13.000 1.5835 0.04251 0.03679 -0.0838 0.1122 0.9043
13.250 1.5811 0.04526 0.03952 -0.0826 0.0996 0.9060
13.500 1.5776 0.04820 0.04241 -0.0816 0.0870 0.9078
13.750 1.5726 0.05139 0.04555 -0.0806 0.0742 0.9097
14.000 1.5676 0.05468 0.04881 -0.0798 0.0618 0.9114
14.250 1.5611 0.05815 0.05225 -0.0790 0.0505 0.9130
14.500 1.5541 0.06169 0.05578 -0.0782 0.0417 0.9144
14.750 1.5477 0.06529 0.05939 -0.0776 0.0354 0.9160
15.000 1.5404 0.06909 0.06321 -0.0771 0.0308 0.9175
15.250 1.5377 0.07242 0.06661 -0.0768 0.0277 0.9191
15.500 1.5303 0.07643 0.07066 -0.0766 0.0253 0.9207
15.750 1.5293 0.07974 0.07408 -0.0767 0.0236 0.9224
16.000 1.5253 0.08350 0.07792 -0.0768 0.0221 0.9240
16.250 1.5175 0.08782 0.08230 -0.0771 0.0209 0.9254
16.500 1.5113 0.09184 0.08644 -0.0773 0.0200 0.9271
16.750 1.5082 0.09551 0.09022 -0.0776 0.0191 0.9291
17.000 1.5036 0.09947 0.09428 -0.0781 0.0184 0.9311
17.250 1.4978 0.10369 0.09859 -0.0788 0.0177 0.9330
17.500 1.4889 0.10840 0.10339 -0.0797 0.0171 0.9347
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